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CIRRUS DESIGN SR20 Pilot Operating Handbook

All-electric sr20 aircraft serials 1268 and subsequent

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Download this manual See also: Pilot Operating Handbook, Maintenance Manual

PILOT'S OPERATING HANDBOOK

AND FAA APPROVED

AIRPLANE FLIGHT MANUAL

for the

CIRRUS DESIGN SR20

A l l - E l e c t r i c S R 2 0

A i r c r a f t S e r i a l s 1 2 6 8 a n d S u b s e q u e n t

FAA Approved in Normal Category based on FAR 23. This document must be carried in

the airplane at all times and be kept within the reach of the pilot during all flight

operations.

THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO

THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY

CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT

MANUAL

Model - Serial Num. SR20-_____________ Registration Num. _ __________________

P/N 11934-003

Reissue A: 10-10-03

Current Revision: A3

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Summary of Contents for CIRRUS DESIGN SR20

Page 1 THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR PART 23 AND ADDITIONAL INFORMATION PROVIDED BY CIRRUS DESIGN AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL Model - Serial Num. SR20-_____________ Registration Num. _ __________________ P/N 11934-003 Reissue A: 10-10-03 Current Revision: A3...
Page 2 Copyright © 2003 - All Rights Reserved Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811...
Page 3 This Pilot’s Operating Handbook (POH or Handbook) has been prepared by Cirrus Design Corporation to familiarize operators with the Cirrus Design SR20 airplane. Read this Handbook carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new”...
Page 4 Pilot’s Operating Handbook Cirrus Design Foreword SR20 The Handbook This Pilot’s Operating Handbook has been prepared using GAMA Specification #1 for Pilot’s Operating Handbook, Revision 2, dated 18 October 1996 as the content model and format guide. However, some deviations from this specification were made for clarity. The Handbook is presented in loose-leaf form for ease in inserting revisions and is sized for convenient storage.
Page 5 Cirrus Design Pilot’s Operating Handbook SR20 Foreword Revising the Handbook Two types of revisions may be issued for this Handbook: Numbered and Temporary. Temporary revisions are printed on yellow paper, normally cover only one topic or procedure, and are issued to provide safety related information or other time sensitive information where the rigor of providing a numbered revision is not possible in the time allowed.
Page 6 Design Supplements produced for this airplane. The “Log of Supplements” page can be utilized as a “Table of Contents” for Section 9. If the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the owner’s responsibility to ensure that the proper supplement, if applicable, is installed in the Handbook and that the supplement is properly recorded on the “Log of...
Page 7 Cirrus Design Pilot’s Operating Handbook SR20 Foreword Retention of Data In the event a new title page is issued, the weight and balance data changes, equipment list changes, or the “Log of Supplements” is replaced, the owner must ensure that all information applicable to the airplane is transferred to the new pages and the aircraft records are current.
Page 8 Pilot’s Operating Handbook Cirrus Design Foreword SR20 Intentionally Left Blank P/N 11934-003 Reissue A...
Page 9: Table Of Contents
Cirrus Design Section 1 SR20 General Section 1 General Table of Contents Introduction ..................1-3 The Airplane..................1-6 Engine..................1-6 Propeller ..................1-6 Fuel....................1-7 Oil ....................1-7 Maximum Certificated Weights ............ 1-7 Cabin and Entry Dimensions ............1-7 Baggage Spaces and Entry Dimensions ........1-7 Specific Loadings.................
Page 10 Section 1 Cirrus Design General SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 11: Introduction
Cirrus Design Section 1 SR20 General Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations.
Page 12 Section 1 Cirrus Design General SR20 26.0' 9.2' 7" NOTE: • Wing span includes position and strobe lights. • Prop ground clearance at 3000 lb - 7" (2 blade), 8" (3 blade). • Wing Area = 135.2 sq. ft. 35.5' 76"...
Page 13 Cirrus Design Section 1 SR20 General GROUND TURNING CLEARANCE 11" -RADIUS FOR WING TIP 11" -RADIUS FOR NOSE GEAR 6" -RADIUS FOR INSIDE GEAR 2" -RADIUS FOR OUTSIDE GEAR TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY A S MUCH AS THREE FEET.
Page 14: The Airplane
Section 1 Cirrus Design General SR20 The Airplane Engine Number of Engines................1 Number of Cylinders................6 Engine Manufacturer ........... Teledyne Continental Engine Model................ IO-360-ES Fuel Metering..............Fuel Injected Engine Cooling ..............Air Cooled Engine Type........Horizontally Opposed, Direct Drive Horsepower Rating..........200 hp @ 2700 rpm...
Page 15: Fuel
Cirrus Design Section 1 SR20 General Fuel Total Capacity..........60.5 U.S. Gallons (229.0 L) Total Usable...........56 U.S. Gallons (212.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Capacity (Sump) ..........8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ..........SAE 15W-50 or 20W-50...
Page 16: Symbols, Abbreviations And Terminology
Section 1 Cirrus Design General SR20 Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level.
Page 17: Meteorological Terminology
Cirrus Design Section 1 SR20 General Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance. Best Rate of Climb Speed is the speed which results in the greatest gain of altitude in a given time.
Page 18: Engine Power Terminology
Section 1 Cirrus Design General SR20 • Standard Temperature is the temperature that would be found at a given pressure altitude in the standard atmosphere. It is 15° C (59° F) at sea level pressure altitude and decreases approximately 2° C (3.6° F) for each 1000 feet of altitude increase.
Page 19: Weight And Balance Terminology
Cirrus Design Section 1 SR20 General • Unusable Fuel is the quantity of fuel that cannot be safely used in flight. • Usable Fuel is the fuel available for flight planning. Weight and Balance Terminology c.g. Center of Gravity is the point at which an airplane would balance if suspended.
Page 20 Section 1 Cirrus Design General SR20 • Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. • Tare is the weight of all items used to hold or position the airplane on the scales for weighing. Tare includes blocks, shims, and chocks.
Page 21 Cirrus Design Section 2 SR20 Limitations Section 2 Limitations Table of Contents Introduction ..................2-3 Certification Status ................2-3 Airspeed Limitations................ 2-4 Airspeed Indicator Markings ............2-5 Power Plant Limitations ..............2-6 Engine..................2-6 Propeller ..................2-7 Instrument Markings ............... 2-8 General Limitations .................
Page 22 Section 2 Cirrus Design Limitations SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 23: Introduction
This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the SR20 and its standard systems and equipment. Refer to Section 9 of this handbook for amended operating limitations for airplanes equipped with optional equipment.
Page 24: Airspeed Limitations
Section 2 Cirrus Design Limitations SR20 Airspeed Limitations The indicated airspeeds in the following table are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 25: Airspeed Indicator Markings
Cirrus Design Section 2 SR20 Limitations Airspeed Indicator Markings The airspeed indicator markings are based upon Section 5 Airspeed Calibrations using the normal static source. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources.
Page 26: Power Plant Limitations
Section 2 Cirrus Design Limitations SR20 Power Plant Limitations Engine Teledyne Continental ............IO-360-ES Power Rating ............200 hp @ 2700 rpm Maximum RPM ...............2700 rpm Oil: Oil Temperature........240° F (115° C) maximum Oil Pressure: Minimum................10 psi Maximum................100 psi...
Page 27: Propeller
Cirrus Design Section 2 SR20 Limitations Propeller • Note • Two-blade propellers are not EASA approved for use on this airplane. Airplanes registered in the European Union should ignore all references to the two-blade propeller in this POH. Hartzell Propeller Type ............. Constant Speed Two-Blade Propeller: Model Number...........
Page 28: Instrument Markings
Section 2 Cirrus Design Limitations SR20 Instrument Markings Red Line Green Arc Yellow Arc Red Line Instrument (Range) Minimum Normal Caution Maximum Power Plant Instruments Tachometer –– 500 - 2700 –– 2700 (0 - 3500 RPM) Cylinder Head –– 240° - 420° F 420° - 460° F 460°...
Page 29: General Limitations
Cirrus Design Section 2 SR20 Limitations General Limitations Weight Limits Maximum Takeoff Weight ......... 3000 lb. (1361 kg) • Note • All weights in excess of 2900 pounds (1315 kg) must consist of wing fuel. Maximum Landing Weight ........2900 lb. (1315 kg) Weight in Baggage Compartment ........
Page 30 Section 2 Cirrus Design Limitations SR20 23.1 % MAC FS 144.1 3000 lb 3000 31.3 % MAC FS 148.0 3000 lb 31.5 % MAC 2800 FS 148.1 16.7 % MAC 2900 lb FS 141.0 2694 lb 2600 16.7 % MAC FS 147.4...
Page 31: Maneuver Limits
Maneuver Limits Aerobatic maneuvers, including spins, are prohibited. • Note • Because the SR20 has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3 – Emergency Procedures, Inadvertent Spiral/Spin Entry.
Page 32: Maximum Occupancy
150° F (66° C), the outer surface of the airplane must be painted with an approved white paint, except for areas of registration marks, placards, and minor trim. Refer to SR20 Airplane Maintenance Manual (AMM), Chapter 51, for specific paint requirements.
Page 33: System Limits
Oxygen System Whenever the operating rules require the use of supplemental oxygen, the pilot must: • Use an oxygen system approved by Cirrus Design and listed in the Oxygen System AFM Supplement Part Number 11934- S09. • Secure the oxygen bottle in the right front seat as described in the AFM Supplement noted above.
Page 34: Kinds Of Operation
Cirrus Design Limitations SR20 Kinds of Operation The SR20 is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Serials 1337 and subsequent with SRV configuration: The airplane is equipped and approved for the following type operations: •...
Page 35 Cirrus Design Section 2 SR20 Limitations Kinds of Operation System, Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Alternator 2 — — Serials 1337 and subsequent with SRV standard configuration: ALT 2 not applicable. Ammeter Low Volts Annunciator ALT 1 Annunciator...
Page 36 Section 2 Cirrus Design Limitations SR20 Kinds of Operation System, Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Roll Trim Indicator Roll Trim System Stall Warning System Fuel Auxiliary Boost Pump Fuel Quantity Indicator Fuel Selector Valve Ice & Rain Protection...
Page 37 Cirrus Design Section 2 SR20 Limitations Kinds of Operation System, Remarks, Instrument, Notes, and/or and/or Equipment Exceptions Attitude Gyro — — — — Turn Coordinator (Gyro) — — Clock — — Nav Radio — — Pitot System Static System, Normal Multi-Function Display —...
Page 38: Placards
Section 2 Cirrus Design Limitations SR20 Placards Engine compartment, inside oil filler access: ENGINE OIL GRADE ABOVE 40° F SAE 50 OR 20W50 BELOW 40° F SAE 30 OR 10W30, 15W50, OR 20W50 REFER TO AFM FOR APPROVED OILS Wing, adjacent to fuel filler caps: AVGAS MIN GRADE 100LL OR 100 28 U.S.
Page 39 Cirrus Design Section 2 SR20 Limitations Upper fuselage, either side of CAPS rocket cover: WARNING! ROCKET FOR PARACHUTE DEPLOYMENT INSIDE STAY CLEAR WHEN AIRPLANE IS OCCUPIED Left fuselage, on external power supply door: Rudder, and elevator, both sides: EXTERNAL NO PUSH...
Page 40 Section 2 Cirrus Design Limitations SR20 Engine control panel: 120 KIAS FLAPS 100% 100 KIAS CREW SEATS MUST BE LOCKED IN POSITION AND CONTROL HANDLES FULLY DOWN BEFORE FLIGHT FULL RICH BOOST FUEL PUMP IDLE CUTOFF PRIME LEFT RIGHT GALLONS...
Page 41 Cirrus Design Section 2 SR20 Limitations Wing, flap aft edge: NO STEP Cabin Door Window, lower edge, centered, applied upside down: RESCUE: FRACTURE AND REMOVE WINDOW Bolster Switch Panel, left edge: THIS AIRCRAFT IS CERTIFIED FOR THE FOLLOWING FLIGHT OPERATIONS:...
Page 42 Section 2 Cirrus Design Limitations SR20 Instrument Panel Upper Right: Bolster Panel, both sides: NO SMOKING GRAB HERE FASTEN SEATBELTS Serials 1351 & subs. Above MFD (on one line): FASTEN SEATBELTS NO SMOKING Cabin Window, above door latch: EMERGENCY EXIT...
Page 43 Cirrus Design Section 2 SR20 Limitations Baggage Compartment, aft edge: ELT LOCATED BEHIND BULKHEAD REMOVE CARPET AND ACCESS PANEL Baggage Compartment Door, inside: DISTRIBUTED FLOOR LIMIT 130 LBS BAGGAGE STRAP CAPACITY IS 35 LBS EACH MAXIMUM SEE AIRPLANE FLIGHT MANUAL FOR BAGGAGE TIE-DOWN...
Page 44 Section 2 Cirrus Design Limitations SR20 CAPS Deployment Handle Cover, above pilot's right shoulder : WARNING USE FOR EXTREME EMERGENCIES ONLY SEAT BELT AND SHOULDER HARNESS MUST BE WORN AT ALL TIMES USE OF THIS DEVICE COULD RESULT IN INJURY OR DEATH...
Page 45 Cirrus Design Section 3 SR20 Emergency Procedures Section 3 Emergency Procedures Table of Contents Introduction ..................3-3 Airspeeds for Emergency Operations ..........3-4 Emergency Procedures Guidance ..........3-5 Preflight Planning................. 3-5 Preflight Inspections/Maintenance ..........3-5 Methodology ................3-5 Ground Emergencies ..............3-7 Engine Fire During Start ..............
Page 46 Section 3 Cirrus Design Emergency Procedures SR20 Landing Without Elevator Control ..........3-24 Landing With Failed Brakes ............3-24 Landing With Flat Tire..............3-25 System Malfunctions ..............3-27 Alternator Failure ...............3-27 LOW VOLTS Warning Light Illuminated ........3-29 Communications Failure ............3-29 Power Lever Linkage Failure .............3-30 Pitot Static Malfunction ..............3-31...
Page 47: Introduction
Emergency Procedures Introduction This section provides procedures for handling emergencies and abnormal situations that may occur while operating the SR20. Although emergencies caused by airplane, systems, or engine malfunctions are extremely rare, the guidelines described in this section should be considered and applied as necessary should an emergency arise.
Page 48: Airspeeds For Emergency Operations
Section 3 Cirrus Design Emergency Procedures SR20 Airspeeds for Emergency Operations Maneuvering Speed: 3000 lb ................131 KIAS 2600 lb ................122 KIAS 2200 lb ................111 KIAS Best Glide: 3000 lb ................96 KIAS 2500 lb ................87 KIAS Emergency Landing (Engine-out): Flaps Up................86 KIAS Flaps 50% ................81 KIAS...
Page 49: Emergency Procedures Guidance
Although this section provides procedures for handling most emergencies and abnormal flight conditions that could arise in the SR20, it is not a substitute for thorough knowledge of the airplane and general aviation techniques. A thorough study of the information in this handbook while on the ground will help you prepare for time-critical situations in the air.
Page 50 Section 3 Cirrus Design Emergency Procedures SR20 Take Appropriate Action — In most situations, the procedures listed in this section will either correct the aircraft problem or allow safe recovery of the aircraft. Follow them and use good pilot judgment.
Page 51: Ground Emergencies
Cirrus Design Section 3 SR20 Emergency Procedures Ground Emergencies Engine Fire During Start A fire during engine start may be caused by fuel igniting in the fuel induction system. If this occurs, attempt to draw the fire back into the engine by continuing to crank the engine.
Page 52: Emergency Engine Shutdown On Ground
Section 3 Cirrus Design Emergency Procedures SR20 even application of the brakes to avoid loss of control and/or a blown tire. Emergency Engine Shutdown On Ground 1. Power Lever ................IDLE 2. Fuel Pump (if used)..............OFF 3. Mixture ................CUTOFF 4.
Page 53: In-Flight Emergencies
Cirrus Design Section 3 SR20 Emergency Procedures In-Flight Emergencies Engine Failure On Takeoff (Low Altitude) If the engine fails immediately after becoming airborne, abort on the runway if possible. If altitude precludes a runway stop but is not sufficient to restart the engine, lower the nose to maintain airspeed and establish a glide attitude.
Page 54: Maximum Glide
Section 3 Cirrus Design Emergency Procedures SR20 Maximum Glide Conditions Example: Power Altitude 7,000 ft. AGL Propeller Windmilling Airspeed Best Glide Flaps 0% (UP) Wind Zero Glide Distance 12.5 NM Best Glide Speed 3000 lb 96 KIAS 2500 lb 87 KIAS Maximum Glide Ratio ~ 10.9 : 1...
Page 55: Engine Failure In Flight
Cirrus Design Section 3 SR20 Emergency Procedures Engine Failure In Flight If the engine fails at altitude, pitch as necessary to establish best glide speed. While gliding toward a suitable landing area, attempt to identify the cause of the failure and correct it.
Page 56: Engine Airstart
Section 3 Cirrus Design Emergency Procedures SR20 Engine Airstart The following procedures address the most common causes for engine loss. Switching tanks and turning the fuel pump on will enhance starting if fuel contamination was the cause of the failure.
Page 57: Engine Partial Power Loss
Cirrus Design Section 3 SR20 Emergency Procedures Engine Partial Power Loss Indications of a partial power loss include fluctuating RPM, reduced or fluctuating manifold pressure, low oil pressure, high oil temperature, and a rough-sounding or rough-running engine. Mild engine roughness in flight may be caused by one or more spark plugs becoming fouled.
Page 58 Section 3 Cirrus Design Emergency Procedures SR20 1. Fuel Pump................BOOST Selecting BOOST on may clear the problem if vapor in the injection lines is the problem or if the engine-driven fuel pump has partially failed. The electric fuel pump will not provide sufficient fuel pressure to supply the engine if the engine-driven fuel pump completely fails.
Page 59: Low Oil Pressure
Cirrus Design Section 3 SR20 Emergency Procedures Low Oil Pressure If low oil pressure is accompanied by a rise in oil temperature, the engine has probably lost a significant amount of its oil and engine failure may be imminent. Immediately reduce engine power to idle and select a suitable forced landing field.
Page 60: Smoke And Fume Elimination
Section 3 Cirrus Design Emergency Procedures SR20 Smoke and Fume Elimination If smoke and/or fumes are detected in the cabin, check the engine instruments for any sign of malfunction. If a fuel leak has occurred, actuation of electrical components may cause a fire. If there is a strong smell of fuel in the cockpit, divert to the nearest suitable landing field.
Page 61: Cabin Fire In Flight
Cirrus Design Section 3 SR20 Emergency Procedures Cabin Fire In Flight If the cause of the fire is readily apparent and accessible, use the fire extinguisher to extinguish flames and land as soon as possible. Opening the vents may feed the fire, but to avoid incapacitating the crew from smoke inhalation, it may be necessary to rid cabin of smoke or fire extinguishant.
Page 62: Inadvertent Icing Encounter
Section 3 Cirrus Design Emergency Procedures SR20 • WARNING • If airplane is in day VFR conditions and turning off the master switches eliminated the fire situation, leave the master switches OFF. Do not attempt to isolate the source of the fire by checking each individual electrical component.
Page 63: Inadvertent Imc Encounter
7. Exit IMC conditions as soon as possible. Door Open In Flight The doors on the SR20 will remain 1-3 inches open in flight if not latched. If this is discovered on takeoff roll, abort takeoff if practical. If already airborne: 1.
Page 64: Spins
Emergency Procedures SR20 Spins The SR20 is not approved for spins, and has not been tested or certified for spin recovery characteristics. The only approved and demonstrated method of spin recovery is activation of the Cirrus Airframe Parachute System (See CAPS Deployment, this section).
Page 65: Caps Deployment
Cirrus Design Section 3 SR20 Emergency Procedures CAPS Deployment The Cirrus Airframe Parachute System (CAPS) should be activated in the event of a life-threatening emergency where CAPS deployment is determined to be safer than continued flight and landing. • WARNING •...
Page 66: Mixture
Section 3 Cirrus Design Emergency Procedures SR20 The maximum demonstrated deployment speed is 135 KIAS. Reducing airspeed allows minimum parachute loads and prevents structural overload and possible parachute failure. 2. Mixture (If time and altitude permit) ......... CUTOFF Generally, a distressed airplane will be safer for its occupants if the engine is not running.
Page 67: Landing Emergencies
Cirrus Design Section 3 SR20 Emergency Procedures 12. Loose Items ..............SECURE If time permits, all loose items should be secured to prevent injury from flying objects in the cabin at touchdown. 13. Assume emergency landing body position. The emergency landing body position is assumed by crossing the arms across the chest, firmly grasping the shoulder harness, and holding the upper torso erect.
Page 68: Emergency Procedures Sr20
Section 3 Cirrus Design Emergency Procedures SR20 2. Radio..........Transmit (121.5 MHz) MAYDAY giving location and intentions 3. Transponder ............SQUAWK 7700 4. If off airport, ELT ............ACTIVATE 5. Power Lever ................IDLE 6. Mixture ................CUTOFF 7. Fuel Selector ................OFF 8.
Page 69: Landing With Flat Tire
Cirrus Design Section 3 SR20 Emergency Procedures Both brakes inoperative 1. Divert to the longest, widest runway with the most direct headwind. 2. Land on downwind side of the runway. 3. Use the rudder for obstacle avoidance. • Note •...
Page 70 Section 3 Cirrus Design Emergency Procedures SR20 AMMETER BAT 1 ALT 1 ALT 2 BATT MAIN DISTRIBUTION ESSENTIAL ALT 1 ALT 2 DISTRIBUTION BUS BAT 2 NON-ESSENTIAL MAIN BUS 2 ESSENTIAL ANNUN SKYWATCH/ FUEL PUMP TAWS TURN TURN COORD. #1 COORD.
Page 71: System Malfunctions
Cirrus Design Section 3 SR20 Emergency Procedures System Malfunctions Alternator Failure Steady illumination of either ALT caution light in the annunciator panel indicates a failure of the corresponding alternator. The most likely the cause of the alternator failure is a wiring fault, a malfunctioning alternator, or a malfunctioning control unit.
Page 72 Section 3 Cirrus Design Emergency Procedures SR20 ALT 1 Light Steady Steady illumination indicates a failure of ALT 1. Attempt to bring alternator back on line. If alternator cannot be brought back, reduce loads and use Main Bus or Non-Essential loads only as necessary for flight conditions.
Page 73: Low Volts Warning Light Illuminated
Cirrus Design Section 3 SR20 Emergency Procedures • Note • ALT 2 light will illuminate steady and ALT 2 will not come on line until 1700 - 2200 RPM. 1. ALT 2 Master Switch ..............OFF 2. Alternator 2 Circuit Breaker ......CHECK and RESET 3.
Page 74: Power Lever Linkage Failure
Section 3 Cirrus Design Emergency Procedures SR20 Power Lever Linkage Failure If the Power Lever linkage fails in flight, the engine will not respond to power lever control movements. Use power available and flaps as required to safely land the airplane.
Page 75: Pitot Static Malfunction
Cirrus Design Section 3 SR20 Emergency Procedures Pitot Static Malfunction Static Source Blocked If erroneous readings of the static source instruments (airspeed, altimeter and vertical speed) are suspected, the alternate static source valve, on side of console near pilot’s right ankle, should be opened to supply static pressure from the cabin to these instruments.
Page 76: Electric Trim/Autopilot Failure
Section 3 Cirrus Design Emergency Procedures SR20 Electric Trim/Autopilot Failure Any failure or malfunction of the electric trim or autopilot can be over- ridden by use of the control yoke. If runaway trim is the problem, de- energize the circuit by pulling the circuit breaker (PITCH TRIM, ROLL TRIM, or AUTOPILOT) and land as soon as conditions permit.
Page 77 Cirrus Design Section 4 SR20 Normal Procedures Section 4 Normal Procedures Table of Contents Introduction ..................4-3 Airspeeds for Normal Operation ............. 4-4 Normal Procedures ................. 4-5 Preflight Inspection ..............4-5 Preflight Walk-Around ..............4-6 Before Starting Engine..............4-9 Starting Engine ................4-10 Before Taxiing................
Page 78 Section 4 Cirrus Design Normal Procedures SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 79: Introduction
Cirrus Design Section 4 SR20 Normal Procedures Introduction This section provides amplified procedures for normal operation. Normal procedures associated with optional systems can be found in Section 9. • Note • Serials 1337 subsequent with standard configuration: The airplane is equipped with a single alternator, dual battery electrical system.
Page 80: Airspeeds For Normal Operation
Section 4 Cirrus Design Normal Procedures SR20 Airspeeds for Normal Operation Unless otherwise noted, the following speeds are based on a maximum weight of 3000 lb. and may be used for any lesser weight. However, to achieve the performance specified in Section 5 for takeoff distance, the speed appropriate to the particular weight must be used.
Page 81: Normal Procedures
Cirrus Design Section 4 SR20 Normal Procedures Normal Procedures Preflight Inspection Before carrying out preflight inspections, ensure that all required maintenance has been accomplished. Review your flight plan and compute weight and balance. • Note • Throughout the walk-around: check all hinges, hinge pins, and bolts for security;...
Page 82: Preflight Walk-Around
Section 4 Cirrus Design Normal Procedures SR20 Preflight Walk-Around 1. Cabin a. Required Documents..........On Board b. Avionics Power Switch............OFF c. Bat 2 Master Switch ............ON d. Avionics Cooling Fan ............ Audible e. Voltmeter ..............23-25 Volts Flap Position Light ............OUT g.
Page 83 Cirrus Design Section 4 SR20 Normal Procedures b. Horizontal and Vertical Stabilizers......Condition c. Elevator and Tab......Condition and Movement d. Rudder..........Freedom of Movement e. Rudder Trim Tab ........Condition and Security Attachment hinges, bolts and cotter pins ......Secure 4. Right Fuselage a.
Page 84 Section 4 Cirrus Design Normal Procedures SR20 8. Nose, Right Side a. Cowling ............ Attachments Secure b. Exhaust Pipe ....Condition, Security, and Clearance c. Transponder Antenna (underside) .. Condition and Attachment d. Gascolator (underside) ....Drain for 3 seconds, Sample 9. Nose gear, Propeller, and Spinner •...
Page 85: Before Starting Engine
Cirrus Design Section 4 SR20 Normal Procedures c. Wheel and Brakes ..Fluid Leaks, Condition, and Security d. Chocks and Tiedown Ropes........Remove e. Fuel Drains (2 underside) ......Drain and Sample Cabin Air Vent............Unobstructed g. Fuel Cap........Check Quantity and Secure h.
Page 86: Starting Engine
Section 4 Cirrus Design Normal Procedures SR20 Starting Engine If the engine is warm, no priming is required. For the first start of the day and in cold conditions, prime will be necessary. • WARNING • If airplane will be started using external power, keep all personnel and power unit cables well clear of the propeller rotation plane.
Page 87 Cirrus Design Section 4 SR20 Normal Procedures • Caution • Limit cranking to intervals of 20 seconds with a 20 second cooling period between cranks. This will improve battery and contactor life. 11. Power Lever ......RETARD (to maintain 1000 RPM) 12.
Page 88: Before Taxiing
Section 4 Cirrus Design Normal Procedures SR20 Before Taxiing 1. Brakes ................CHECK 2. Flaps ................. UP (0%) 3. Radios/Avionics............AS REQUIRED 4. Cabin Heat/Defrost ..........AS REQUIRED Taxiing When taxiing, maintain directional control with rudder and differential braking. In crosswind conditions, some brake force may be required, even when taxiing at moderate speeds.
Page 89 Cirrus Design Section 4 SR20 Normal Procedures 3. Doors ................LATCHED 4. Brakes................... HOLD 5. Flight Controls..........FREE & CORRECT 6. Trims ................SET Takeoff 7. Autopilot ..............DISCONNECT 8. Flaps ............... SET 50% & CHECK 9. Flight and Engine Instruments ........... CHECK 10.
Page 90: Takeoff
Section 4 Cirrus Design Normal Procedures SR20 15. Voltage ................CHECK 16. Magnetos ............ CHECK Left and Right a. Ignition Switch ......... R, note RPM, then BOTH b. Ignition Switch ........L, note RPM, then BOTH • Note • RPM drop must not exceed 150 RPM for either magneto. RPM differential must not exceed 75 RPM between magnetos.
Page 91: Normal Takeoff
Cirrus Design Section 4 SR20 Normal Procedures over an obstacle than do takeoffs with no flaps. Takeoff flap settings greater than 50% are not approved. Soft or rough field takeoffs are performed with 50% flaps by lifting the airplane off the ground as soon as practical in a tail-low attitude. If no obstacles are ahead, the airplane should be leveled off immediately to accelerate to a higher climb speed.
Page 92: Climb
Section 4 Cirrus Design Normal Procedures SR20 Climb Normal climbs are performed flaps UP (0%) and full power at speeds 5 to 10 knots higher than best rate-of-climb speeds. These higher speeds give the best combination of performance, visibility and engine cooling.
Page 93: Cruise
Cirrus Design Section 4 SR20 Normal Procedures Cruise Normal cruising is performed between 55% and 75% power. The engine power setting and corresponding fuel consumption for various altitudes and temperatures can be determined by using the cruise data in Section 5.
Page 94: Cruise Leaning
Section 4 Cirrus Design Normal Procedures SR20 Cruise Leaning The engine is equipped with an altitude compensating fuel pump that automatically provides the proper full rich mixture. Because of this, the mixture should be set to full rich to allow the aneroid to provide auto leaning for the engine during all flight conditions.
Page 95: Descent
Cirrus Design Section 4 SR20 Normal Procedures Descent 1. Altimeter................... SET 2. Cabin Heat/Defrost ..........AS REQUIRED 3. Fuel System ............... CHECK 4. Mixture ..............AS REQUIRED 5. Flaps ..............AS REQUIRED 6. Brake Pressure ..............CHECK Before Landing 1. Seat Belt and Shoulder Harness ........SECURE 2.
Page 96: Balked Landing/Go-Around
Section 4 Cirrus Design Normal Procedures SR20 Short Field Landing For a short field landing in smooth air conditions, make an approach at 75 KIAS with full flaps using enough power to control the glide path (slightly higher approach speeds should be used under turbulent air conditions).
Page 97: After Landing
Cirrus Design Section 4 SR20 Normal Procedures After Landing 1. Flaps ..................UP 2. Power Lever ..............1000 RPM 3. Transponder ................STBY • Note • As the airplane slows the rudder becomes less effective and taxiing is accomplished using differential braking.
Page 98: Stalls
Normal Procedures SR20 Stalls SR20 stall characteristics are conventional. Power-off stalls may be accompanied by a slight nose bobbing if full aft stick is held. Power-on stalls are marked by a high sink rate at full aft stick. Power-off stall speeds at maximum weight for both forward and aft C.G.
Page 99: Environmental Considerations
Cirrus Design Section 4 SR20 Normal Procedures Environmental Considerations Cold Weather Operation Starting If the engine has been cold soaked, it is recommended that the propeller be pulled through by hand several times to break loose or limber the oil. This procedure will reduce power draw on the battery if a battery start is made.
Page 100 Section 4 Cirrus Design Normal Procedures SR20 • WARNING • If airplane will be started using external power, keep all personnel and power unit cables well clear of the propeller rotation plane. Refer to Section 8 - Ground Handling, Servicing, and Maintenance for special procedures and precautions when using external power.
Page 101 Cirrus Design Section 4 SR20 Normal Procedures 14. Alt Master Switches ..............ON 15. Avionics Power Switch ...............ON 16. Engine Parameters ............MONITOR 17. External Power (If applicable) ......... DISCONNECT 18. Ammeter ................CHECK 19. Strobe Lights................ON • Note • If the engine does not start during the first few attempts, or if engine firing diminishes in strength, the spark plugs have probably frosted over.
Page 102: Hot Weather Operation
Fuel BOOST should be left ON during takeoff and for climb as required for vapor suppression with hot or warm fuel. Noise Characteristics/Abatement The certificated noise levels for the Cirrus Design SR20 established in accordance with FAR 36 Appendix G are: Configuration...
Page 103: Fuel Conservation
Cirrus Design Section 4 SR20 Normal Procedures Fuel Conservation Minimum fuel use at cruise will be achieved using the best economy power setting described under cruise. P/N 11934-003 4-27 Revision A2...
Page 104 Section 4 Cirrus Design Normal Procedures SR20 Intentionally Left Blank 4-28 P/N 11934-003 Revision A2...
Page 105 Cirrus Design Section 5 SR20 Performance Data Section 5 Performance Data Table of Contents Introduction ..................5-3 Associated Conditions Affecting Performance......5-3 Flight Planning ................5-4 Sample Problem ................5-4 Takeoff..................5-5 Climb.................... 5-6 Cruise ..................5-7 Fuel Required ................5-8 Landing ..................
Page 106 Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile ............5-29 Balked Landing Climb Gradient ............5-30 Balked Landing Rate of Climb............5-31 Landing Distance ................5-32 Landing Distance ................5-33 P/N 11934-003 Revision A3...
Page 107: Introduction
Cirrus Design Section 5 SR20 Performance Data Introduction Performance data in this section are presented for operational planning so that you will know what performance to expect from the airplane under various ambient and field conditions. Performance data are presented for takeoff, climb, and cruise (including range &...
Page 108: Flight Planning
Section 5 Cirrus Design Performance Data SR20 Flight Planning The performance tables in this section present sufficient information to predict airplane performance with reasonable accuracy. However, variations in fuel metering, mixture leaning technique, engine & propeller condition, air turbulence, and other variables encountered during a particular flight may account for variations of 10% or more in range and endurance.
Page 109: Takeoff
Cirrus Design Section 5 SR20 Performance Data • Expected wind enroute........10 Knot Headwind Landing Conditions: • Field pressure altitude ..........2000 Feet • Temperature ..........20° C (ISA + 10° C) • Field length..............3000 Feet Takeoff The takeoff distance tables, Figure 5-9, show the takeoff ground roll and horizontal distance to reach 50 feet above ground level.
Page 110: Climb
Section 5 Cirrus Design Performance Data SR20 manner as the wind correction above. Refer to Figure 5-9 for correction factors to be applied. Climb The takeoff and enroute rate-of-climb and climb gradient tables, Figures 5-10 through 5-13, present maximum rate of climb and climb gradient for various conditions.
Page 111 Cirrus Design Section 5 SR20 Performance Data The fuel estimate for climb is: • Fuel to climb (standard temperature) ......2.1 Gal. • Increase due to non-standard temp. (2.1 x 0.13) ..0.3 Gal. • Corrected fuel to climb (2.1 + 0.3) ......... 2.4 Gal.
Page 112: Fuel Required
Section 5 Cirrus Design Performance Data SR20 Fuel Required The total fuel requirement for the flight may be estimated using the performance information obtained from Figures 5-14 and 5-15. The resultant cruise distance is: • Total distance (from sample problem) ......560.0 NM •...
Page 113: Landing
Cirrus Design Section 5 SR20 Performance Data Landing A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-19 presents landing distance information for the short field technique. The distances corresponding to 2000 feet and 20° C are as follows: •...
Page 114: Airspeed Calibration
Section 5 Cirrus Design Performance Data SR20 Airspeed Calibration Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....85 Knots • Weight ........3000 LB Calibrated Airspeed ..... 86 Knots •...
Page 115: Airspeed Calibration
Cirrus Design Section 5 SR20 Performance Data Airspeed Calibration Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........50% continuous, whichever is less. Indicated Airspeed....85 Knots • Weight ........3000 LB • Heater, Defroster & Vents .....ON Calibrated Airspeed ....84 Knots •...
Page 116: Altitude Correction
Section 5 Cirrus Design Performance Data SR20 Altitude Correction Normal Static Source Conditions: Example: • Power for level flight or maximum Flaps ........... 50% continuous, whichever is less. Indicated Airspeed ....85 Knots • Weight ........3000 LB Desired Altitude....12,000 FT Altitude Correction .....-7 FT...
Page 117: Altitude Correction
Cirrus Design Section 5 SR20 Performance Data Altitude Correction Alternate Static Source Conditions: Example: • Power for level flight or maximum Flaps..........0% continuous, whichever is less. Indicated Airspeed....120 Knots • Weight ........3000 LB Desired Altitude ....12,000 FT • Heater, Defroster, & Vents.....ON Altitude Correction....
Page 118: Temperature Conversion
Section 5 Cirrus Design Performance Data SR20 Temperature Conversion • Note • • To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.
Page 119: Outside Air Temperature For Isa Condition
Cirrus Design Section 5 SR20 Performance Data Outside Air Temperature ISA Condition Example: Pressure Altitude....8000 FT Outside Air Temp....... 48° F ISA Condition ....ISA + 10° C Press ISA-40°C ISA-20°C ISA+10°C ISA+20°C Feet °C °F °C °F °C °F °C...
Page 120: Stall Speeds
Section 5 Cirrus Design Performance Data SR20 Stall Speeds Conditions: Example: • Weight ........3000 LB Flaps ........Up (0%) • C.G........... Noted Bank Angle........15° • Power..........Idle • Bank Angle ....... Noted Stall Speed..66 KIAS | 68 KCAS •...
Page 121: Wind Components
Cirrus Design Section 5 SR20 Performance Data Wind Components Conditions: Example: • Runway Heading ......10° Wind/Flight Path Angle ....50° • Wind Direction.......60° Crosswind Component ..12 Knots • Wind Velocity......15 Knots Headwind Component..10 Knots • Note • • The maximum demonstrated crosswind is 21 knots. Value not considered limiting.
Page 122: Takeoff Distance
Section 5 Cirrus Design Performance Data SR20 Takeoff Distance Conditions: Example: • Winds.......... Zero Outside Air Temp ....... 25°C • Runway....Dry, Level, Paved Weight........3000 LB • Flaps........... 50% Pressure Altitude....2000 FT • Power........Maximum Headwind ......12 Knots set before brake release Runway ......
Page 123 Cirrus Design Section 5 SR20 Performance Data Takeoff Distance WEIGHT = 3000 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 68 KIAS knots headwind. Speed over 50 Ft. Obstacle = 75 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 124: Takeoff Distance
Section 5 Cirrus Design Performance Data SR20 Takeoff Distance WEIGHT = 2500 LB Headwind: Subtract 10% for each 12 Speed at Liftoff = 65 KIAS knots headwind. Speed over 50 Ft Obstacle = 70 KIAS Tailwind: Add 10% for each 2 knots Flaps - 50% ·...
Page 125: Takeoff Climb Gradient
Cirrus Design Section 5 SR20 Performance Data Takeoff Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3000 LB • Flaps ........... 50% Pressure Altitude ....1750 FT •...
Page 126: Takeoff Rate Of Climb
Section 5 Cirrus Design Performance Data SR20 Takeoff Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture........Full Rich Weight........3000 LB • Flaps........... 50% Pressure Altitude....1750 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 127: Enroute Climb Gradient
Cirrus Design Section 5 SR20 Performance Data Enroute Climb Gradient Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........3000 LB • Flaps ........0% (UP) Pressure Altitude ....4200 FT •...
Page 128: Enroute Rate Of Climb
Section 5 Cirrus Design Performance Data SR20 Enroute Rate of Climb Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 10° C • Mixture........Full Rich Weight........3000 LB • Flaps........0% (UP) Pressure Altitude....6500 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 129: Time, Fuel And Distance To Climb
Cirrus Design Section 5 SR20 Performance Data Time, Fuel and Distance to Climb Conditions: Example: • Power ......Full Throttle Outside Air Temp ......ISA • Mixture ......... Full Rich Weight ........3000 LB • Fuel Density .....6.0 LB/GAL Airport Press ......1000 FT •...
Page 130: Cruise Performance
Section 5 Cirrus Design Performance Data SR20 Cruise Performance Conditions: Example: • Mixture......Best Power Outside Air Temp ...... 29° C • Cruise Weight ....... 2600 LB RPM ......... 2700 RPM • Winds.......... Zero Cruise Press Alt ....8000 FT Note: % Power (22.2 MAP)....
Page 131 Cirrus Design Section 5 SR20 Performance Data Cruise Performance 8000 Feet Pressure Altitude ISA - 30° C (-31° C) ISA (-1° C) ISA + 30° C (29° C) KTAS KTAS KTAS 2700 22.2 12.9 11.6 11.4 2500 22.2 11.4 11.0 10.6...
Page 132: Range / Endurance Profile
Section 5 Cirrus Design Performance Data SR20 Range / Endurance Profile Conditions: Example: • Weight ........3000 LB Power Setting ......65% • Temperature ....Standard Day Takeoff Press Alt ....2000 FT • Winds.......... Zero Cruise Press Alt ....6000 FT •...
Page 133: Performance Data
Cirrus Design Section 5 SR20 Performance Data Range / Endurance Profile 65% POWER Mixture = Best Power Press Climb Fuel Airspeed Fuel Endurance Range Specific Fuel Remaining Flow Range For Cruise KTAS Hours Nm/Gal 46.3 10.5 13.0 2000 45.7 10.5 13.1...
Page 134: Balked Landing Climb Gradient
Section 5 Cirrus Design Performance Data SR20 Balked Landing Climb Gradient Conditions: Example: • Power.......Full Throttle Outside Air Temp ...... 20° C • Mixture........Full Rich Weight........2500 LB • Flaps.........100% (DN) Pressure Altitude....2000 FT • Airspeed ....Best Rate of Climb Climb Airspeed.....
Page 135: Balked Landing Rate Of Climb
Cirrus Design Section 5 SR20 Performance Data Balked Landing Rate of Climb Conditions: Example: • Power ......Full Throttle Outside Air Temp .......20° C • Mixture ......... Full Rich Weight ........2500 LB • Flaps ........ 100% (DN) Pressure Altitude ....4000 FT •...
Page 136: Landing Distance
Section 5 Cirrus Design Performance Data SR20 Landing Distance Conditions: Example: • Technique ......Normal Outside Air Temp ....... 10°C • Winds.......... Zero Weight........2900 LB • Runway........Paved Pressure Altitude....2000 FT • Flaps......... 100% Headwind ........Zero • Power....3° Power Approach to 50 FT obstacle, Landing Ground Roll .....
Page 137 Cirrus Design Section 5 SR20 Performance Data Landing Distance WEIGHT = 2900 LB Headwind: Subtract 10% per each Speed over 50 Ft Obstacle = 75 KIAS 13 knots headwind. Flaps - 100% · Idle · Dry, Level Paved Surface Tailwind: Add 10% for each 2 knots tailwind up to 10 knots.
Page 138 Section 5 Cirrus Design Performance Data SR20 Intentionally Left Blank 5-34 P/N 11934-003 Reissue A...
Page 139 Cirrus Design Section 6 SR20 Weight and Balance Section 6 Weight and Balance Table of Contents Introduction ..................6-3 Airplane Weighing Form ..............6-6 Airplane Weighing Procedures ............6-7 Weight & Balance Record ............. 6-10 Loading Instructions ..............6-12 Center of Gravity Limits ..............6-14 Weight &...
Page 140 Section 6 Cirrus Design Weight and Balance SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 141: Introduction
Cirrus Design Section 6 SR20 Weight & Balance Introduction This section describes the procedure for establishing the basic empty weight and moment of the airplane. Sample forms are provided for reference. Procedures for calculating the weight and moment for various operations are also provided. A comprehensive list of all equipment available for this airplane is included at the back of this section.
Page 142 Section 6 Cirrus Design Weight & Balance SR20 350.2" WATER LINE (WL) 165.5" 222.0" 100.0" 55.6" 38.3" WL100 NOTE Reference Datum located at fuselage station 0.0". 157.5" (FS) FUSELAGE STATION LEMAC FS 132.9" RBL 210.9" RBL 87.7" MAC 48.4" Typical LBL RBL 77.3"...
Page 143 Cirrus Design Section 6 SR20 Weight & Balance Figure 6-2 Airplane Leveling P/N 11934-003 Revision A2...
Page 144: Airplane Weighing Form
Section 6 Cirrus Design Weight & Balance SR20 Airplane Weighing Form REF DATUM FS 0.0 FS 100.0 FS 145.0 WL 100.0 A = x + 100 B = A - y y = ____________ Measured x = ____________ Measured SR20_FM06_1441...
Page 145: Airplane Weighing Procedures
Cirrus Design Section 6 SR20 Weight & Balance Airplane Weighing Procedures A basic empty weight and center of gravity were established for this airplane when the airplane was weighed just prior to initial delivery. However, major modifications, loss of records, addition or relocation of...
Page 146 Section 6 Cirrus Design Weight & Balance SR20 4. Measuring (Figure 6-3): a. Obtain measurement ‘x’ by measuring horizontally along the airplane center line (BL 0) from a line stretched between the main wheel centers to a plumb bob dropped from the forward side of the firewall (FS 100).
Page 147 Cirrus Design Section 6 SR20 Weight & Balance The above procedure determines the airplane Basic Empty Weight, moment, and center of gravity in inches aft of datum. C.G. can also be expressed in terms of its location as a percentage of the airplane Mean Aerodynamic Cord (MAC) using the following formula: ÷...
Page 148: Weight & Balance Record
Section 6 Cirrus Design Weight & Balance SR20 Weight & Balance Record Use this form to maintain a continuous history of changes and modifications to airplane structure or equipment affecting weight and balance: Serial Num: Reg. Num: Page Item Weight Change...
Page 149 38.5" 25.0" 16.0" 20.0" 10.5" 32.0" 39.0" 33.4" 20.0" 33.3" 5.0" 21.0" CABIN DOOR BAGGAGE DOOR OPENING OPENING SR20 FM06 1019 Location Length Width Height Volume Cabin 122” 49.3” 49.7 137 cu ft Baggage 36” 39.8” 38.5” 32 cu ft...
Page 150: Loading Instructions
Section 6 Cirrus Design Weight & Balance SR20 Loading Instructions It is the responsibility of the pilot to ensure that the airplane is properly loaded and operated within the prescribed weight and center of gravity limits. The following information enables the pilot to calculate the total weight and moment for the loading.
Page 151 Cirrus Design Section 6 SR20 Weight & Balance • The total moment/1000 must not be above the maximum or below the minimum moment/1000 for the Takeoff Condition Weight as determined from the Moment Limits chart or table (Figure 6-9). P/N 11934-003...
Page 152: Center Of Gravity Limits
Section 6 Cirrus Design Weight & Balance SR20 Center of Gravity Limits The charts below depict the airplane center-of-gravity envelope in terms of inches aft of the reference datum and as a percentage of the Mean Aerodynamic Cord (MAC). The relationship between the two is detailed in the weighing instructions.
Page 153: Weight & Balance Loading Form
Cirrus Design Section 6 SR20 Weight & Balance Weight & Balance Loading Form Serial Num: ________________ Date: ________________________ Reg. Num: _________________ Initials: ______________________ Weight Moment/ Item Description 1000 Basic Empty Weight Includes unusable fuel & full oil Front Seat Occupants Pilot &...
Page 154: Loading Data
Section 6 Cirrus Design Weight & Balance SR20 Loading Data Use the following chart or table to determine the moment/1000 for fuel and payload items to complete the Loading Form (Figure 6-7). Fuel Fwd Pass Loading Chart Aft Pass Baggage...
Page 155: Moment Limits
Cirrus Design Section 6 SR20 Weight & Balance Moment Limits Use the following chart or table to determine if the weight and moment from the completed Weight and Balance Loading Form (Figure 6-7) are within limits. 3000 2800 2600 2400...
Page 156: Equipment List
Section 6 Cirrus Design Weight & Balance SR20 Equipment List This list will be determined after the final equipment has been installed in the aircraft. 6-18 P/N 11934-003 Reissue A...
Page 157 Cirrus Design Section 7 SR20 Airplane Description Section 7 Airplane and Systems Description Table of Contents Introduction ..................7-5 Airframe ..................7-6 Fuselage ..................7-6 Wings................... 7-6 Empennage ................. 7-7 Wing Flaps ..................7-8 Flap Control Switch..............7-8 Primary Flight Controls ..............7-10 Elevator System.................
Page 158 Section 7 Cirrus Design Airplane Description SR20 Engine Fuel Ignition ..............7-32 Engine Exhaust................7-33 Engine Controls .................7-33 Alternate Air Control..............7-34 Engine Indicating ...............7-34 Propeller ..................7-38 Fuel System ..................7-39 Fuel Caution Light..............7-41 Fuel Quantity Indicator...............7-41 Fuel Selector Valve..............7-42 Boost Pump Switch..............7-42 Electrical System................7-43 Power Generation ..............7-43...
Page 159 Section 7 Cirrus Design Airplane Description SR20 Altimeter..................7-59 Pitot Heat Switch ............... 7-59 Pitot Heat Light ................7-60 Alternate Static Source .............. 7-60 Avionics and Navigation..............7-61 Avionics Power Switch............... 7-63 Magnetic Compass ..............7-63 Directional Gyro - Serials 1268 thru 1336........7-63 Turn Coordinator - Serials 1268 thru 1336 ........
Page 160 Section 7 Cirrus Design Airplane Description SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 161: Introduction
Cirrus Design Section 7 SR20 Airplane Description Introduction This section provides a basic description and operation of the standard airplane and its systems. Optional equipment described within this section is identified as optional. • Note • Some optional equipment, primarily avionics, may not be described in this section.
Page 162: Airframe
SR20 Airframe Fuselage The SR20 monocoque fuselage is constructed primarily of composite materials and is designed to be aerodynamically efficient. The cabin area is bounded on the forward side by the firewall at fuselage station 100, and on the rear by the aft baggage compartment bulkhead at fuselage station 222.
Page 163: Empennage
Cirrus Design Section 7 SR20 Airplane Description fuselage. The main wing spar passes under the fuselage below the two front seats and is attached to the fuselage in two locations. The rear shear webs are attached to the fuselage sidewalls just aft of the rear seats.
Page 164: Wing Flaps
Section 7 Cirrus Design Airplane Description SR20 Wing Flaps The electrically controlled, single-slotted flaps provide low-speed lift enhancement. Each flap is manufactured of aluminium and connected to the wing structure at three hinge points. Rub strips are installed on the top leading edge of each flap to prevent contact between the flap and wing flap cove.
Page 165 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1460 Figure 7-1 Flap Control System P/N 11934-003 Reissue A...
Page 166: Primary Flight Controls
Airplane Description SR20 Primary Flight Controls The SR20 uses conventional flight controls for ailerons, elevator and rudder. The control surfaces are pilot controlled through either of two single-handed side control yokes mounted beneath the instrument panel. The location and design of the control yokes allow easy, natural use by the pilot.
Page 167 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1461 Figure 7-2 Elevator Control System P/N 11934-003 7-11 Reissue A...
Page 168: Aileron System
Section 7 Cirrus Design Airplane Description SR20 Aileron System The ailerons provide airplane roll control. The ailerons are of conventional design with skin, spar and ribs manufactured of aluminum. Each aileron is attached to the wing shear web at two hinge points.
Page 169 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1462 Figure 7-3 Aileron Control System P/N 11934-003 7-13 Reissue A...
Page 170: Rudder System
Control Locks The Cirrus SR20 control system is not equipped with gust locks. The trim spring cartridges have sufficient power to act as a gust damper without rigidly locking the position.
Page 171 Cirrus Design Section 7 SR20 Airplane Description SR20_FM07_1463 Figure 7-4 Rudder Control System P/N 11934-003 7-15 Reissue A...
Page 172: Trim Systems
Section 7 Cirrus Design Airplane Description SR20 Trim Systems Roll and pitch trim are provided by adjusting the neutral position of a compression spring cartridge in each control system by means of an electric motor. The electric roll trim is also used by the autopilot to position the ailerons.
Page 173: Yaw Trim System
Cirrus Design Section 7 SR20 Airplane Description Yaw Trim System Yaw trim is provided by spring cartridge attached to the rudder pedal torque tube and console structure. The spring cartridge provides a centering force regardless of the direction of rudder deflection. The yaw trim is ground adjustable only.
Page 174: Flight Deck Arrangement
A large color multifunction display is located between the flight instruments and the engine instruments. Temperature controls are located on the right side below the engine instruments. The SR20 uses standard flight instruments arranged in the ‘basic-six’ pattern. They include: Airspeed Indicator Attitude Gyro...
Page 175: Center Console
Cirrus Design Section 7 SR20 Airplane Description sensors, the System 55X/55SR Autopilot, and is the primary heading source for the Multifunction Display. The PFD replaces the following instruments: • HSI • Vertical Speed Indicator • VOR/LOC Indicator • Altitude Alerter •...
Page 176 Section 7 Cirrus Design Airplane Description SR20 TEMP C 15 20 1500 1400 AIRSPEED U C T I O ALTIMETER KNOTS CIRRUS I N H TRIM ST HD VERTICAL TURN COORDINATO R SPEED 2 MIN ALT AIR PULL ON ALT STATIC...
Page 177 Cirrus Design Section 7 SR20 Airplane Description FASTEN SEATBELTS NO SM OKING ALTITUDE GPH 16000 12000 8000 4000 MAX POWER FUEL FLOWS AMMETER SELECT ALT 1 ALT 2 BATT ALT AIR PULL ON ALT STATIC SOURCE NORMAL PARK BRAKE PULL ON...
Page 178: Airplane Cabin
Section 7 Cirrus Design Airplane Description SR20 Airplane Cabin Cabin Doors • Caution • Serials 1423 and subsequent: The seat back must be in the fully upright or the fully reclined position before closing the cabin door. Seat backs in the forward or break-over position can cause damage to the door handle or interior panel.
Page 179 Cirrus Design Section 7 SR20 Airplane Description DEFROST AIR OUTLETS STALL WARNING HORN FIRE EXTINGUISHER (UNDER PILOT'S SEAT) OVERHEAD LIGHT AND SWITCH DOOR HANDLE EGRESS HAMMER (IN ARMREST) CABIN SPEAKER PASSENGER FRESH AIR OUTLET OVERHEAD LIGHT AND SWITCH TIEDOWN LOOPS...
Page 180: Seats
Section 7 Cirrus Design Airplane Description SR20 Four baggage tie-down straps are provided to secure baggage and other items loaded in the baggage compartment. Each strap assembly has a hook at each end and a cam-lock buckle in the middle. The hook ends clip over loop fittings installed in the baggage floor and in the aft bulkhead.
Page 181 Cirrus Design Section 7 SR20 Airplane Description To position front seat fore and aft: 1. Lift the position control handle. 2. Slide the seat into position. 3. Release the handle and check that the seat is locked in place. To adjust recline position: 1.
Page 182: Cabin Safety Equipment
Section 7 Cirrus Design Airplane Description SR20 Cabin Safety Equipment Passenger Restraints Integrated seat belt and shoulder harness assemblies with inertia reels are provided for the pilot and each passenger. The rear seat belts are attached to fittings on the floorboard and the forward seat belts are attached to the seat frame.
Page 183 Cirrus Design Section 7 SR20 Airplane Description Emergency Egress Hammer An eight-ounce ball-peen type hammer is located in the center armrest accessible to either front seat occupant. In the event of a mishap where the cabin doors are jammed or inoperable, the hammer may be used to break through the acrylic windows to provide an escape path for the cabin occupants.
Page 184: Landing Gear
Section 7 Cirrus Design Airplane Description SR20 Landing Gear Main Gear The main landing gear are bolted to composite wing structure between the wing spar and shear web. The landing gear struts are constructed of composite material for fatigue resistance. The composite construction is both rugged and maintenance free.
Page 185 Cirrus Design Section 7 SR20 Airplane Description weak braking action. Should any of these symptoms occur, immediate maintenance is required. If, during taxi or landing roll, braking action decreases, let up on the pedals and then reapply the brakes with heavy pressure.
Page 186 Section 7 Cirrus Design Airplane Description SR20 RESERVOIR MIL-H-5606 FLUID ONLY RUDDER PEDAL(4) MASTER CYLINDER(4) PARKING PARKING BRAKE BRAKE VALVE KNOB CALIPER CALIPER ASSEMBLY ASSEMBLY ROTOR ROTOR (DISK) (DISK) SR20_FM07_1015 Figure 7-7 Brake System 7-30 P/N 11934-003 Reissue A...
Page 187: Engine
SR20 Airplane Description Engine The SR20 is powered by a Teledyne Continental IO-360-ES, six- cylinder, normally aspirated, fuel-injected engine de-rated to 200 hp at 2,700 RPM. The engine has a 2000-hour Time Between Overhaul (TBO). Dual, conventional magnetos provide ignition.
Page 188: Engine Fuel Injection
Section 7 Cirrus Design Airplane Description SR20 the engine compartment through two vents in the aft portion of the cowling. No movable cowl flaps are used. Engine Fuel Injection The multi-nozzle, continuous-flow fuel injection system supplies fuel for engine operation. An engine driven fuel pump draws fuel from the selected wing tank and passes it to the mixture control valve integral to the pump.
Page 189: Engine Exhaust
Cirrus Design Section 7 SR20 Airplane Description Engine Exhaust Engine exhaust gases are routed through a dual tuned exhaust system. After leaving the cylinders, exhaust gases are routed through the exhaust manifold, through mufflers located on either side of the engine, and then overboard through exhaust pipes exiting through the lower cowling.
Page 190: Alternate Air Control
Engine Indicating The SR20 is equipped with engine instruments and warning lights to monitor the engine performance. The instruments are located on the right side of the instrument panel and the warning lights are located in the annunciator panel immediately in front of the pilot.
Page 191 Cirrus Design Section 7 SR20 Airplane Description DETAIL B Alternate Air Control DETAIL A Start / Ignition Switch 1500 1400 Fuel Pump FUEL Left Right DETAIL D DETAIL C Engine Instruments Controls LEGEND 1. Tachometer 6. Power Lever 7. Mixture Control 2.
Page 192 Section 7 Cirrus Design Airplane Description SR20 Oil Warning Light The red OIL warning light in the annunciator panel comes on to indicate either high oil temperature or low oil pressure. The light is illuminated by a switch in the oil temperature gage if the oil temperature reaches 240°...
Page 193 Cirrus Design Section 7 SR20 Airplane Description temperature sensor mounted in the 2 cylinder head on the left side of the engine. Oil Temperature / Oil Pressure Gage A 2¼” combination Oil Temperature and Oil Pressure indicator is mounted on the right instrument panel immediately below the EGT/ CHT indicator.
Page 194: Propeller
Section 7 Cirrus Design Airplane Description SR20 Propeller The airplane is equipped with a constant-speed, aluminum-alloy propeller with a governor. The airplane is available with the standard two-blade (76” diameter) propeller or an optional three-blade (74” diameter) propeller. The propeller governor automatically adjusts propeller pitch to regulate propeller and engine RPM.
Page 195: Fuel System
Cirrus Design Section 7 SR20 Airplane Description Fuel System A 56-gallon usable wet-wing fuel storage system provides fuel for engine operation. The system consists of a 30.3-gallon capacity (28- gallon usable) vented integral fuel tank in each wing, a fuel collector/ sump in each wing, a three-position selector valve, an electric boost pump, and an engine-driven fuel pump.
Page 196 Section 7 Cirrus Design Airplane Description SR20 ANNUNCIATOR FUEL FUEL QUANTITY VENT VENT FILLER FILLER INDICATOR L. WING TANK R. WING TANK R. WING L. WING COLLECTOR COLLECTOR SELECTOR VALVE FLAPPER FLAPPER VALVE VALVE DRAIN (5 PLACES) FIREWALL BOOST ELECTRIC...
Page 197: Fuel Caution Light
Cirrus Design Section 7 SR20 Airplane Description The airplane may be serviced to a reduced capacity to permit heavier cabin loadings. This is accomplished by filling each tank to a tab visible below the fuel filler, giving a reduced fuel load of 13 gallons usable in each tank (26 gallons total usable in all flight conditions).
Page 198: Fuel Selector Valve
Section 7 Cirrus Design Airplane Description SR20 • Note • When the fuel tanks are 1/4 full or less, prolonged uncoordinated flight such as slips or skids can uncover the fuel tank outlets. Therefore, if operating with one fuel tank dry...
Page 199: Electrical System
Power Generation Primary power for the SR20 is supplied by a 28-VDC, negative-ground electrical system. The electrical power generation system consists of two alternators controlled by a Master Control Unit (MCU) mounted on the left side of the firewall and two batteries for starting and electrical power storage.
Page 200 Section 7 Cirrus Design Airplane Description SR20 222) below the parachute canister. BAT 2 is charged from the circuit breaker panel Essential Bus. The Master Control Unit (MCU) is located on the left firewall. The MCU controls ALT 1, ALT 2, starter, landing light, external power, and power generation functions.
Page 201 Cirrus Design Section 7 SR20 Airplane Description ALT 1 RELAY ALT 1 VOLT REG LANDING LIGHT ALT 1 SWITCH LANDING LIGHT SWITCH ALT 2 BAT 1 SWITCH BAT 1 VOLT REG FUEL VOLTS PITOT ALT 1 ALT 2 HEAT MASTER CONTROL UNIT...
Page 202: Power Distribution
Airplane Description SR20 Power Distribution The power distribution system for the SR20 consists of the main distribution bus and the essential distribution bus in the MCU and associated buses in the Circuit Breaker panel. The circuit breaker panel is located on the left side of the console next to the pilots right knee.
Page 203: Avionics Power Switch
Cirrus Design Section 7 SR20 Airplane Description is indicated. When the BAT 1 switch is set to ‘on,’ the remaining systems will be energized. To check or use avionics equipment or radios while on the ground, the AVIONICS power switch must also be turned on.
Page 204: Volt / Amp Meter
Section 7 Cirrus Design Airplane Description SR20 • Note • The LOW VOLTS warning light may come on during extended low RPM operation with heavy electrical loads. Under these conditions, the light will go out at higher RPM. Volt / Amp Meter A 2¼”...
Page 205: Circuit Breakers And Fuses
Cirrus Design Section 7 SR20 Airplane Description and current sensors on the ALT 1 and ALT 2 output lines. Steady illumination of either light indicates an alternator failure. A flashing ALT light indicates an overcurrent condition. Circuit Breakers and Fuses...
Page 206: Ground Service Receptacle
Section 7 Cirrus Design Airplane Description SR20 the MCU Main Distribution Bus through a 25-amp circuit breaker. ALT 2 and BAT 2 are prevented from powering the Non-Essential Equipment Bus by the isolation diode interconnecting the MCU distribution buses. Loads on the Non-Essential Equipment Bus are shed by pulling the individual circuit breakers.
Page 207: Exterior Lighting
Cirrus Design Section 7 SR20 Airplane Description Exterior Lighting The airplane is equipped with standard wing tip and tail-mounted navigation lights with integral anti-collision strobe lights. The separately controlled landing light is located in the lower cowl. Navigation Lights The airplane is equipped with standard wing tip navigation lights. The lights are controlled through the NAV light switch on the instrument panel bolster.
Page 208: Interior Lighting
Section 7 Cirrus Design Airplane Description SR20 Interior Lighting Interior lighting for the airplane consists of separately controlled incandescent overhead lights for general cabin lighting, individual lights for the pilots and passengers, and dimmable panel floodlights. The flight instruments and avionics equipment lights are dimmable.
Page 209: Environmental System
Cirrus Design Section 7 SR20 Airplane Description panel bolster. Rotating the knob clockwise from the off position will illuminate the light and control its intensity. The lights are powered by 28 VDC supplied through the 3-amp CABIN LIGHTS circuit breaker on Main Bus 2.
Page 210: Heating And Ventilation
Section 7 Cirrus Design Airplane Description SR20 AIR INLET HEAT MUFF HVAC PLENUM CABIN HEAT/ HEAT DEFROST SELECT TEMP. CONTROL COLD WINDSHIELD DEFROST DIFFUSER FRESH AIR FRESH AIR CREW INTAKE INTAKE OUTLETS CREW OUTLETS PASSENGER PASSENGER OUTLET OUTLET FRESH AIR...
Page 211: Cabin Heat Control
Cirrus Design Section 7 SR20 Airplane Description Cabin Heat Control The amount of heated air allowed into the air mixing plenum is controlled by rotating the Cabin Heat Control, located inboard of the Cabin Air Selector. The control is mechanically linked to a door in a heater box between the heater muff and the mixing plenum.
Page 212: Stall Warning System
Section 7 Cirrus Design Airplane Description SR20 Stall Warning System The airplane is equipped with an electro-pneumatic stall warning system to provide audible warning of an approach to aerodynamic stall. The system consists of an inlet in the leading edge of the right wing, a pressure switch and associated plumbing, and a piezo- ceramic horn behind the instrument panel.
Page 213 Cirrus Design Section 7 SR20 Airplane Description AIRSPEED VERTICAL SPEED INDICATOR INDICATOR ALTIMETER TEMP C° VERTICAL AIRSPEED SPEED ALTITUDE 3 KNOTS ALTITUDE DIGITIZER ALTITUDE TRANSDUCER (OPTIONAL) ALTERNATE STATIC AIR SOURCE PITOT-STATIC WATER TRAPS PITOT MAST STATIC HEATER BUTTONS CURRENT PITOT...
Page 214: Pitot-Static System
Section 7 Cirrus Design Airplane Description SR20 Pitot-Static System The Pitot-Static system consists of a single heated Pitot tube mounted on the left wing and dual static ports mounted in the fuselage. The Pitot heat is pilot controlled through a panel-mounted switch. An internally mounted alternate static pressure source provides backup static pressure should that the primary static source becomes blocked.
Page 215: Altimeter
Cirrus Design Section 7 SR20 Airplane Description from zero and descent is indicated by counter clockwise rotation. The ‘0’ (zero) reference point is at the 9 o’clock position. The scale is calibrated from 0 to 2000 FPM in 100-FPM increments in both the ‘UP’...
Page 216: Pitot Heat Light
Section 7 Cirrus Design Airplane Description SR20 Pitot Heat Light Illumination of the amber PITOT HEAT caution light indicates that the Pitot Heat switch is in the ‘on’ position and the Pitot heater is not receiving electrical current. A current sensor on the Pitot heater power supply wire provides current sensing.
Page 217: Avionics And Navigation
Section 7 SR20 Airplane Description Avionics and Navigation • Note • The following paragraphs and equipment descriptions describe the standard avionics in the SR20. For detailed descriptions specific avionic equipment, operating procedures, or data for optional avionic equipment, refer to the...
Page 218 Section 7 Cirrus Design Airplane Description SR20 • Marker Beacon Receiver (Garmin GMA 340) • Two IFR Approach-Certified GPS (Garmin GNS 430 and Garmin GNS 420) • Two VHF Communications Transceivers (Garmin GNS 430 and Garmin GNS 420) • Single Navigation (VOR/LOC/GS) Receiver (GNS 430) •...
Page 219: Avionics Power Switch
Cirrus Design Section 7 SR20 Airplane Description • Mode C Transponder with Altitude Encoder (Garmin GTX 327) Avionics Configuration SRV - Serials 1337 and subsequent: • Primary Flight Display (Avidyne PFD) • Moving Map Display (Avidyne MFD) • Integrated Audio System with Intercom (Garmin GMA 340) •...
Page 220: Turn Coordinator - Serials 1268 Thru 1336
Section 7 Cirrus Design Airplane Description SR20 1. Push and hold knob at lower left corner of instrument. 2. While holding knob in, rotate knob to adjust gyro compass dial with current magnetic heading. 3. Release knob. Turn Coordinator - Serials 1268 thru 1336 Avionics Configuration 2.0 and 2.1:...
Page 221: Course Deviation Indicator - Serials 1268 Thru 1336
Cirrus Design Section 7 SR20 Airplane Description reference lines useful for pitch attitude control. The indicator can follow maneuvers through 360° in roll and 360° in pitch. A knob at the bottom of the instrument allows adjustment of the miniature airplane to the horizon bar for a more accurate flight attitude indication.
Page 222: Horizontal Situation Indicator - Serials 1268 Thru 1336
Section 7 Cirrus Design Airplane Description SR20 Horizontal Situation Indicator - Serials 1268 thru 1336 Avionics Configuration 2.1: The Century NSD-1000 is a conventional HSI that provides gyro stabilized, magnetically slaved, heading information, a pictorial VOR/ LOC display with a conventional course arrow, and glideslope presentation.
Page 223 Cirrus Design Section 7 SR20 Airplane Description amp HSI/PFD 1 circuit breaker on the Essential Bus and the 5-amp HSI/PFD 2 circuit breaker on Main Bus 2. Either circuit is capable of powering the Navigation Display. The full-color display uses a rear-projection system driven by an active matrix LCD display.
Page 224: Autopilot
Bus 2. Autopilot Avionics Configuration 2.0: The standard SR20 is equipped with an S-TEC System Twenty Autopilot. This single-axis autopilot system is a rate-based system, deriving roll axis control inputs from its electric turn coordinator. The programmer, computer, annunciators, and servo amplifier are contained entirely within the turn coordinator case.
Page 225 Cirrus Design Section 7 SR20 Airplane Description operates on 28 VDC supplied through the 5-amp AUTOPILOT circuit breaker on the Essential Bus. The S-Tec System Thirty Autopilot features: • Roll Stabilization; • Turn Command; • NAV/LOC/GPS tracking; HI and LO sensitivity;...
Page 226 Section 7 Cirrus Design Airplane Description SR20 through the 5-amp AUTOPILOT circuit breaker on the Essential Bus. The S-Tec System 55X Autopilot features: • Heading Hold and Command; • NAV/LOC/GPS/GS tracking, high and low sensitivity, and automatic 45° -course intercept;...
Page 227: Audio System
Cirrus Design Section 7 SR20 Airplane Description • GPS Steering (GPSS) for smoother turns onto a course or during course tracking. Audio System The Garmin GMA 340 audio control unit, located in the center console, provides audio amplification, audio selection, marker beacon control, and a voice activated intercom system for the cabin speaker, headsets, and microphones.
Page 228: Multi-Function Display
Section 7 Cirrus Design Airplane Description SR20 Multi-Function Display This airplane is equipped with the Avidyne FlightMax EX-Series Multi- Function Display (MFD). The moving map display provides visual advisory of the airplane’s GPS position against a moving map. This information supplements CDI or HSI course deviation and is advisory only.
Page 229: Gps Navigation
Cirrus Design Section 7 SR20 Airplane Description GPS Navigation The Jeppesen Navigation Database provides access to data on Airports, Approaches, Standard Instrument Departures (SIDs), Standard Terminal Arrivals (STARs), VORs, NDBs, Intersections, Minimum Safe Altitudes, Controlled Airspace Advisories and Frequencies. North American and International databases are available.
Page 230: Communication (Com) Transceivers
Section 7 Cirrus Design Airplane Description SR20 in the center console. The panels include function keys, power switches, MSG and NAV status annunciators, a color LCD display (GNS 430), two concentric selector knobs on each panel, and a Jeppesen NavData card slot in each panel. The displays are daylight readable and automatically dimmed for low-light operation.
Page 231 Cirrus Design Section 7 SR20 Airplane Description 720-channel (25 kHz spacing) or 2280-channel (8.33 kHz spacing) operation in a frequency range from 118.000 to 136.975 MHz. The COM 1 antenna is located above the cabin on the airplane centerline. 28 VDC for COM 1 transceiver operation is controlled through the Avionics Master Switch on the bolster switch panel and supplied through the 7.5-amp COM 1 circuit breaker on the Essential Avionics...
Page 232: Navigation (Nav) Receiver
Section 7 Cirrus Design Airplane Description SR20 COM 1 antenna is located above the cabin on the airplane centerline. 28 VDC for COM 1 transceiver operation is controlled through the Avionics Master Switch on the bolster switch panel and supplied through the 7.5-amp COM 1 circuit breaker on the Essential Avionics...
Page 233: Transponder
Cirrus Design Section 7 SR20 Airplane Description and LOC is provided to the audio system. The Nav antenna, mounted on top of the vertical tail, provides VOR/LOC input for both Nav receivers. NAV 1 – The upper GARMIN GNS 430 is designated NAV 1. 28 VDC...
Page 234: Emergency Locator Transmitter
Section 7 Cirrus Design Airplane Description SR20 Emergency Locator Transmitter The airplane is equipped with a self-contained emergency locator transmitter (ELT). The transmitter and antenna are installed immediately behind the aft cabin bulkhead to the right of the airplane centerline. The main transmitter control switch, labeled ON-OFF- ARMED, on the transmitter is in the armed position for normal operations.
Page 235: Hour Meter
Cirrus Design Section 7 SR20 Airplane Description a. Remove access at lower aft center of baggage compartment. b. Disconnect fixed antenna lead from front of unit. c. Disconnect lead from remote switch and indicator unit. d. Loosen attach straps and remove transmitter unit and portable antenna.
Page 236 Section 7 Cirrus Design Airplane Description SR20 will display Local Time (LT), and Elapsed Time (ET) sequentially. Pressing the button again will return the display to UT. Set UT or LT: Use the Select button to select UT or LT as desired. Simultaneously press Select and Control buttons (tens of hours LED will flash).
Page 237 Cirrus Design Section 7 SR20 Airplane Description OAT – VOLTS Button Serials 1005 and subsequent without Avionics Configuration PFD; The red OAT-VOLTS button is used to display Outside Air Temperature and airplane main bus voltage. When the airplane is powered down, the upper display will display the clock’s back-up battery voltage.
Page 238: Cirrus Airplane Parachute System
Airplane Description SR20 Cirrus Airplane Parachute System The SR20 is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. The system is intended to...
Page 239: Activation Handle
Cirrus Design Section 7 SR20 Airplane Description sequence the slider limits the initial diameter of the parachute and the rate at which the parachute inflates. As the slider moves down the suspension lines the canopy inflates. A three-point harness connects the airplane fuselage structure to the parachute.
Page 240: Deployment Characteristics
Section 7 Cirrus Design Airplane Description SR20 Attempting to activate the rocket by pushing the activation T- handle forward and down limits the force that can be applied. Pulling the activation T-handle straight down generates the greatest force. A maintenance safety pin is provided to ensure that the activation handle is not pulled during maintenance.
Page 241 Cirrus Design Section 7 SR20 Airplane Description equal to the velocity of the surface wind. In addition, surface winds may continue to drag the aircraft after ground impact. • Caution • Ground impact is expected to be equivalent to touchdown from a height of approximately 10 feet.
Page 242 Section 7 Cirrus Design Airplane Description SR20 Intentionally Left Blank 7-86 P/N 11934-003 Reissue A...
Page 243 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Section 8 Handling, Servicing, Maintenance Table of Contents Introduction ..................8-3 Operator’s Publications ..............8-3 Service Publications ..............8-3 Ordering Publications ..............8-4 Airplane Records and Certificates ..........8-5 Airworthiness Directives..............8-6 Airplane Inspection Periods ............8-7 Pilot Performed Preventative Maintenance .........
Page 244 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Instrument Panel and Electronic Display Screens .....8-31 Headliner and Trim Panels ............8-31 Leather Upholstery and Seats ...........8-32 Carpets ..................8-32 P/N 11934-003 Revision A3...
Page 245: Introduction
Introduction This section provides general guidelines for handling, servicing and maintaining your Cirrus Design SR20. In order to ensure continued safe and efficient operation of your airplane, keep in contact with your Authorized Cirrus Service Center to obtain the latest information pertaining to your aircraft.
Page 246: Ordering Publications
SR20 publications, revision service, service publication subscription service may be obtained by contacting Customer Service at Cirrus Design as follows: Cirrus Design Corporation Customer Service 4515 Taylor Circle Duluth, MN 55811 Phone: 218 727-2737 FAX: 218 727-2148 Make sure to include airplane serial number and owner’s name in all correspondence for accurate processing of your documentation needs.
Page 247: Airplane Records And Certificates
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Airplane Records and Certificates The Federal Aviation Administration (FAA) requires that certain data, certificates, and licenses be displayed or carried aboard the airplane at all times. Additionally, other documents must be made available upon request.
Page 248: Airworthiness Directives
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Airworthiness Directives The Federal Aviation Administration (FAA) publishes Airworthiness Directives (AD’s) that apply to specific aircraft and aircraft appliances or accessories. AD’s are mandatory changes and must be complied with within a time limit set forth in the AD. Operators should periodically check with Cirrus Service Centers or A&P mechanic to...
Page 249: Airplane Inspection Periods
Powerplant (A&P) mechanic holding an Inspection Authorization (IA). All Cirrus Authorized Service Centers can perform annual inspections. The inspection is listed, in detail, in Chapter 5 of the Cirrus Design SR20 Maintenance Manual. If the airplane is used commercially, in addition to the annual inspection requirement, the regulation requires that the airplane undergo a 100-hour inspection each 100 hours of flight operation.
Page 250: Pilot Performed Preventative Maintenance
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Pilot Performed Preventative Maintenance The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43, Appendix A. This maintenance may be performed only on an aircraft that the pilot owns or operates and which is not used in air carrier service.
Page 251 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance • Clean or replace fuel and oil strainers, as well as replace or clean filter elements. • Replace prefabricated fuel lines. • Replace the battery and check fluid level and specific gravity.
Page 252: Ground Handling
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Ground Handling Application of External Power A ground service receptacle, located just aft of the cowl on the left side of the airplane, permits the use of an external power source for cold weather starting and maintenance procedures.
Page 253: Towing
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed in the rear baggage compartment or by power equipment that will not damage or excessively strain the nose gear assembly.
Page 254: Taxiing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Taxiing Before attempting to taxi the airplane, ground personnel should be instructed and authorized by the owner to taxi the airplane. Instruction should include engine starting and shutdown procedures in addition to taxi and steering techniques.
Page 255: Parking
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Parking The airplane should be parked to protect the airplane from weather and to prevent it from becoming a hazard to other aircraft. The parking brake may release or exert excessive pressure because of heat buildup after heavy braking or during wide temperature swings.
Page 256: Tiedown
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Tiedown The airplane should be moored for immovability, security and protection. FAA Advisory Circular AC 20-35C, Tiedown Sense, contains additional information regarding preparation for severe weather, tiedown, and related information. The following procedures should be used for the proper mooring of the airplane: 1.
Page 257: Jacking
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Jacking Two jacking points are provided: one at each wing tiedown. Jack points (pads) are stowed in the baggage compartment. The airplane may be jacked using two standard aircraft hydraulic jacks at the wing jacking points and a weighted tailstand attached to the tail tiedown.
Page 258: Servicing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Servicing Landing Gear Servicing The main landing gear wheel assemblies use 15 x 6.00 x 6, six-ply rating tires and tubes. The nose wheel assembly uses a 5.00 x 5 four- ply rating, type III tire and tube. Always keep tires inflated to the rated pressure to obtain optimum performance and maximum service.
Page 259: Tire Inflation
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance 2. Check brake linings for deterioration and maximum permissible wear. Replace lining when worn to 0.100 inch (2.54 mm). 3. Install main landing gear fairings. Tire Inflation For maximum service from the tires, keep them inflated to the proper pressure.
Page 260: Oil Servicing
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Oil Servicing The oil capacity of the Teledyne Continental IO-360-ES engine is 8 quarts. It is recommended that the oil be changed every 50 hours and sooner under unfavorable operating conditions. The following grades...
Page 261 • Caution • MIL-C-6529, Type II straight mineral oil with corrosion preventive can cause coking with extended use and is not recommended by Cirrus Design for break-in or post break-in use. After 25 hours of operation and after oil consumption has stabilized,...
Page 262 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Product Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Shell Canada Ltd. Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50 Aeroshell Oil W Shell Oil Company Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W50...
Page 263: Fuel System Servicing
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Fuel System Servicing At every 100-hours of operation, the fuel filtration screen in the gascolator must be cleaned. After cleaning, a small amount of grease applied to the gascolator bowl gasket will facilitate reassembly.
Page 264 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 3. Place rubber protective cover over wing around fuel filler. • Note • Do not permit fuel nozzle to come in contact with bottom of fuel tanks. Keep fuel tanks at least half full at all times to minimize condensation and moisture accumulation in tanks.
Page 265: Fuel Contamination And Sampling
The remainder of the fuel may be drained by opening the drain valves. Use the same precautions as when refueling airplane. Refer to the SR20 Maintenance Manual for specific procedures.
Page 266: Battery Service
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Battery Service Access to the 24 volt Battery 1 is gained by removing the upper cowl. It is mounted to the forward right side of the firewall. The battery vent is connected to an acid resistant plastic tube that vents gases and electrolyte overflow overboard.
Page 267: Cleaning And Care
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning and Care Cleaning Exterior Surfaces • Note • Prior to cleaning, place the airplane in a shaded area to allow the surfaces to cool. The airplane should be washed with a mild soap and water. Harsh abrasives or alkaline soaps or detergents could make scratches on painted or plastic surfaces or could cause corrosion of metal.
Page 268: Windscreen And Windows
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Windscreen and Windows Before cleaning an acrylic window, rinse away all dirt particles before applying cloth or chamois. Never rub dry acrylic. Dull or scratched window coverings may be polished using a special acrylic polishing paste.
Page 269: Engine Compartment
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Engine Compartment Before cleaning the engine compartment, place a strip of tape on the magneto vents to prevent any solvent from entering these units. 1. Place a large pan under the engine to catch waste.
Page 270: Landing Gear
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Landing Gear Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. 1. Place a pan under the gear to catch waste. 2. Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as desired.
Page 271 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Mild Dishwasher Soap Fuselage Exterior and Any Source (abrasive free) Landing Gear Pure Carnauba Wax Fuselage Exterior Any Source Mothers California Gold Fuselage Exterior Wal-Mart Stores Pure Carnauba Wax...
Page 272: Cleaning Interior Surfaces
Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Cleaning Interior Surfaces Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles.
Page 273: Instrument Panel And Electronic Display Screens
Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Instrument Panel and Electronic Display Screens The instrument panel, control knobs, and plastic trim need only to be wiped clean with a soft damp cloth. The multifunction display, primary flight display, and other electronic display screens should be cleaned with Optimax - LCD Screen Cleaning Solution as follows: •...
Page 274: Leather Upholstery And Seats
2. Wipe leather upholstery with a soft, damp cloth. 3. Soiled upholstery, may be cleaned with the approved products available from Cirrus Design. Avoid soaking or harsh rubbing. Carpets To clean carpets, first remove loose dirt with a whiskbroom or vacuum.
Page 275 Cirrus Design Section 8 SR20 Handling, Servicing, Maintenance Cleaning Product Cleaning Application Supplier Interior Windscreen and Prist Prist Aerospace Windows Optimax Display Screens PhotoDon Mild Dishwasher Soap Cabin Interior Any Source (abrasive free) Leather Care Kit Leather Upholstery Cirrus Design...
Page 276 Section 8 Cirrus Design Handling, Servicing, Maintenance SR20 Intentionally Left Blank 8-34 P/N 11934-003 Revision A3...
Page 277 Supplements This section of the handbook contains FAA Approved Supplements necessary to safely and to efficiently operate the SR20 when equipped with optional systems or equipment not provided with the standard airplane or for special operations or not included in the handbook.
Page 278 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 11934-003 Reissue A...
Page 279 This Log of Supplements shows all Cirrus Design Supplements available for the SR20 at the date shown in the lower left corner. A check mark (✓) in the Part Number column in- dicates that the corresponding supplement is installed in this POH.
Page 280 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank P/N 11934-003 Revision A3...
Page 281 Garmin GMA 340 Audio System When the Garmin GMA 340 Audio Panel is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook (Handbook). Information in this supplement either adds to, supersedes, or deletes information in the basic Handbook.
Page 282 Section 9 Cirrus Design Supplements SR20 Section 1 - General This supplement provides detailed operating instructions for the Garmin GMA 340 Audio Selector Panel/Intercom System with internal Marker Beacon. This supplement covers the basic operating areas of the Audio Control Panel.
Page 283 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No change from basic Handbook. Section 3 - Emergency Procedures In the event of an audio panel power failure, the audio system will revert to COM 1 for the pilot’s mic and headphones and the pilot will have transmit and receive capability.
Page 284 Section 9 Cirrus Design Supplements SR20 Audio/Transceiver Selection Audio selection is performed through the eight selector push buttons in the center of the Audio Control Panel. All audio selector push buttons are push-on, push-off. Selecting an audio source supplies audio to the headphones or cabin speaker.
Page 285 Cirrus Design Section 9 SR20 Supplements COM Swap Mode COM swap mode is not available in this installation. Speaker Output Pressing the SPKR button will cause the selected airplane radios to be heard over the cabin speaker. Speaker output is muted when a COM microphone is keyed.
Page 286 Section 9 Cirrus Design Supplements SR20 • When both the PILOT and CREW ICS Isolation mode are not selected, MUSIC1 is available to crew and passengers. Radio activity, MKR activity, and ICS activity will mute Music1. Intercom Intercom controls are located towards the left side of the Audio Control Panel.
Page 287 Cirrus Design Section 9 SR20 Supplements the frustration of clipping the first syllables. There is a slight delay after a person stops talking before the channel closes. This prevents closure between words and eliminates choppy communications. To adjust squelch: 1. With the engine running, set the VOX trip level by slowly rotating the SQL control knob clockwise until you no longer hear the engine noise in the headphones.
Page 288 Section 9 Cirrus Design Supplements SR20 The following table shows, in abbreviated form, what each occupant hears in each of the selectable Intercom modes: Mode Pilot Hears Copilot Hears Passenger Hears PILOT A/C Radios Passengers Passengers Pilot Copilot Copilot Music1...
Page 289 Cirrus Design Section 9 SR20 Supplements Marker beacon light and audio keying for ILS approach are summarized below: O (Blue) Outer Marker light and associated 400 Hertz tone. The light and tone are keyed at a rate of two tones/flashes per second.
Page 290 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 10 of 10 P/N 11934-S01 Revised: 07-03-04...
Page 291 VHF COM When a Garmin GNC 250XL GPS Navigator with VHF COM is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 292 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a Garmin GNC 250XL GPS Navigator with VHF COM, herein referred to as the “Navigator.” The GNC 250XL utilizes the Global Positioning System (GPS) satellite network to derive the airplane’s position (latitude, longitude, and altitude) and the...
Page 293 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. The Garmin GNC 250XL Pilot's Guide and Reference, P/N 190- 00067-60, Revision A dated March 1997 (or later appropriate revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the GPS Navigator.
Page 294 • Note • This supplement provides a general description of the Garmin GNC 250XL, its operation, and SR20 interface. For a detailed description of the GNC 250XL and full operation instructions refer to the Garmin GNC 250XL Pilot's Guide and Reference, P/N 190-00067-60, Revision A dated March 1997 (or later appropriate revision).
Page 295 Cirrus Design Section 9 SR20 Supplements GNC 250XL Integrated GPS/NAV/COM System This airplane is equipped with a GNC 250XL integrated GPS navigator and COM receiver. The GPS navigator consists of a GPS receiver and a Jeppesen NavData database all contained in the GNC 250XL control unit mounted in the center console.
Page 296 Section 9 Cirrus Design Supplements SR20 Communication (COM) Transceiver 250XL includes digitally-tuned integrated communications (COM) transceiver. The transceiver and integrated controls are mounted in the Garmin GNC 250XL unit and are designated COM2. The transceiver receives all narrow- and wide- band VHF communication transmissions transmitted within a frequency range of 118.000 MHz to 136.975 MHz in 25.0 kHz steps...
Page 297 S-Tec System Twenty Autopilot When the S-Tec System Twenty Autopilot is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 298 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with an S-TEC System Twenty Autopilot. This single-axis autopilot system is a rate-based system, deriving roll axis control inputs from its integral electric turn coordinator. The programmer, computer/amplifier, and annunciators are contained entirely within the turn coordinator case.
Page 299 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Autopilot operation is prohibited above 180 KIAS. 2. The autopilot must not be engaged for takeoff or landing. 3. The autopilot must be disconnected in moderate or severe turbulence.
Page 300 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and its modes. Autopilot Pre-Flight Test 1. Battery Master Switch ............... ON 2. Avionics Power Switch .............. ON Note that all autopilot annunciators, except TRIM UP and DN, illuminate.
Page 301 Cirrus Design Section 9 SR20 Supplements c. Use Autopilot Mode Selector to engage TRK HI mode and move OBS so that VOR deviation needle moves left or right. Note that control yokes follow direction of needle movement with more authority than in TRK LO mode.
Page 302 Section 9 Cirrus Design Supplements SR20 GPS Tracking and GPS Approach 1. Begin with a reliable GPS signal and CDI course needle centered, with airplane on the suggested heading to the waypoint. • Note • The airplane must be within 5° of the desired course when TRK is selected.
Page 303 Cirrus Design Section 9 SR20 Supplements Section 7 - Systems Description The airplane is equipped with an S-Tec System Twenty single-axis Automatic Flight Control System (Autopilot). The autopilot is a pure rate autopilot that uses an inclined gyro in the turn coordinator case as the primary turn and roll rate sensor.
Page 304 Section 9 Cirrus Design Supplements SR20 Depressing either control yoke trim switch will also disengage the autopilot. ST (Stabilizer) Mode - Turning the Mode Select Knob left or right in ST (Stabilizer) mode will provide left/right steering commands to the autopilot proportional to the knob displacement.
Page 305 (FAR Part 91 or FAR Part 135), this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook (Handbook). Information in this supplement either adds to, supersedes, or deletes information in the basic Handbook.
Page 306 Section 1 - General This supplement lists the approved portable oxygen systems that may be used in the SR20 when supplemental oxygen is required by the applicable operating rules, as well as provides mounting instructions and general operating procedures for all approved systems.
Page 307 Cirrus Design Section 9 SR20 Supplements Section 3 - Emergency Procedures Smoke and Fume Elimination In addition to the procedures outlined in the basic Handbook, pilot and passengers should don cannulas or masks and use oxygen at the maximum flow rate until smoke and fumes have cleared.
Page 308 Section 9 Cirrus Design Supplements SR20 Descent After airplane descends through altitude requiring oxygen: 1. Oxygen Shutoff Valve...............OFF 2. Pilot and passengers ......Stow Masks or Cannulas Section 5 - Performance No change from basic Handbook. Section 6 - Weight & Balance The weight, arm, and moment for fully charged systems (1800 –...
Page 309 Cirrus Design Section 9 SR20 Supplements INITIAL INSTALLATION Clip strap to triangular loop as shown in Detail A. Route strap over headrest, down TUFF PACK BAG the back of the seat, and forward between the cushion and seat back. Clip strap to lower triangular loop.
Page 310 Section 9 Cirrus Design Supplements SR20 OXYGEN DURATION - HOURS Fully Charged System (1800 psig at 70° F) Number of Altitude ~ Feet System Persons Typical Using O 10,000 15,000 18,000 (Liters) 2.23 1.49 1.24 XCP-180 1.12 0.75 0.62 (134) 0.74...
Page 311 Sensor When the BF Goodrich Aerospace WX500 Stormscope Sensor is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 312 Section 9 Cirrus Design Supplements SR20 Section 1 General This airplane is equipped with a BF Goodrich Aerospace WX500 Stormscope Sensor. The stormscope sensor output is displayed on the ARNAV ICDS 2000 Multi-function display (MFD). Section 2 - Limitations 1. Stormscope information displayed on the ARNAV ICDS 2000 Multi-function display is FOR REFERENCE ONLY and must not be used for navigation.
Page 313 Cirrus Design Section 9 SR20 Supplements Section 5 - Performance There is no change to the airplane performance when the WX500 stormscope is installed. Section 6 - Weight & Balance Weight and balance data for the WX500 stormscope is provided with the Equipment List for each delivered airplane.
Page 314 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 4 of 4 P/N 11934-S11 Original: 04-12-00...
Page 315 FAA Approved Airplane Flight Manual Supplement Garmin GTX 327 Transponder When a Garmin GTX 327 Transponder is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 316 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a single Garmin GTX 327 ATC Mode A/ C (identification and altitude) transponder with squawk capability. This supplement provides complete operating instructions for the GTX 327 and does not require any additional data be carried in the airplane.
Page 317 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations No Change Section 3 - Emergency Procedures No Change Section 4 - Normal Procedures • Note • Expected coverage from the GTX 327 is limited to “line of sight.” Low altitude or aircraft antenna shielding by the airplane itself may result in reduced range.
Page 318 • Note • This supplement provides specific procedures for use of the GTX 327 Transponder in the SR20 and a general description of the unit. For a detailed description of the GTX 327, refer to GARMIN GTX 327 Mode A/C Transponder Pilots Guide, p/n 190-00187-00 Revision A (Feb 2000) or later revision.
Page 319 Cirrus Design Section 9 SR20 Supplements Mode Selector Keys The mode selector keys are located in a circular arrangement immediately to the left of the display window. The selected mode is annunciated at the left side of the display immediately adjacent to the selector keys.
Page 320 Section 9 Cirrus Design Supplements SR20 Code Selector Keys Code selection is accomplished by depressing the eight selector keys (numbered 0 - 7) located immediately below the display. Any of 4096 active identification codes can be selected. The selected code must be in accordance with instructions for IFR flight or rules applicable to transponder utilization for VFR flight.
Page 321 Cirrus Design Section 9 SR20 Supplements Reply Light The reply light is the small reverse video “R” immediately below the mode annunciation in the display window. The reply light will blink each time the transponder replies to ground interrogations. The light will remain on during the 18-second IDENT time interval.
Page 322 Section 9 Cirrus Design Supplements SR20 COUNT DOWN TIMER - The count down timer is controlled by the START / STOP key. The CRSR and “0 - 9” keys are used to set the initial time. Pressing the CLR key resets the timer to the initial value.
Page 323 Advisory System When the Goodrich SkyWatch 497 is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the appropriate Cirrus Design Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 324 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with a Goodrich SkyWatch SKY497 Traffic Advisory System to advise the pilot of transponder-equipped aircraft that may pose a collision threat. SkyWatch advisory information is displayed on the GARMIN 430 display. The display indicates relative range, bearing, and altitude of intruder aircraft.
Page 325 Cirrus Design Section 9 SR20 Supplements Section 4 - Normal Procedures After Engine Start 1. Avionics Power Switch ...............ON 2. SkyWatch will turn on, complete a self-test, and then enter the STBY mode. • Note • During the takeoff run, SkyWatch will automatically switch to operational mode approximately 8 seconds after 35 KIAS is achieved.
Page 326 Section 9 Cirrus Design Supplements SR20 1. Turn the cursor on and highlight STBY. 2. Use the small PUSH CRSR knob to select OPER? 3. Press the ENT key to place SkyWatch in the OPER (operational) mode. SkyWatch will switch into the 6 nmi display range.
Page 327 Cirrus Design Section 9 SR20 Supplements Section 5 - Performance No Change Section 6 - Weight & Balance SkyWatch adds the following optional (Sym = O) equipment at the weight and arm shown in the following table. ATA/ Unit Description...
Page 328 Section 9 Cirrus Design Supplements SR20 The SkyWatch System consists of a Transmitter Receiver Computer (TRC) installed under the copilot’s seat just forward of the spar tunnel and a directional antenna installed on the airplane exterior above the cabin. The system also utilizes inputs from the altitude encoder, the aircraft heading system (gyro slaving amplifier), and a speed switch plumbed into the pitot system.
Page 329 Supplement Cirrus Design SR20 Airplanes Registered in Canada 1. This supplement is required for operation of Cirrus Design SR20 airplane serial numbers 1100 and subsequent when registered in Canada. This supplement must be attached to the applicable SR20 FAA-approved Airplane Flight Manual (P/N 11934-001 dated 31 Mar 1999 or P/N 11934-002 dated 20 Aug 2001 or later FAA-approved Flight Manual revision).
Page 330 Section 9 Cirrus Design Supplements SR20 Weight Conversion Kilograms Into Pounds Kilograms En Livres 11.0 13.2 15.4 17.6 19.8 22.0 24.3 26.5 28.7 30.9 33.1 35.3 37.5 39.6 41.9 44.1 46.3 48.5 50.7 52.9 55.1 57.3 59.5 61.7 63.9 66.1 68.3...
Page 331 Cirrus Design Section 9 SR20 Supplements Weight Conversion Kilograms x 2.205 = Pounds Pounds x 0.454 = Kilograms POUNDS KILOGRAMS Units x 10, 100, etc SR20_FM09_1510 Figure - 1 Sheet 2 of 2 P/N 11934-S17 3 of 14 Original: 10-10-01...
Page 332 Section 9 Cirrus Design Supplements SR20 Length Conversion Metres Into Feet Metres En Pieds 13.1 16.4 19.7 23.0 26.3 29.5 32.8 36.1 39.4 42.7 45.9 49.2 52.5 55.8 59.1 62.3 65.6 68.9 72.2 75.5 78.7 82.0 85.3 88.6 91.9 95.1 98.4...
Page 333 Cirrus Design Section 9 SR20 Supplements Length Conversion Metres x 3.281 = Feet Feet x 0.305 = Metres FEET METRES Units x 10, 100, etc SR20_FM09_1511 Figure - 2 Sheet 2 of 4 P/N 11934-S17 5 of 14 Original: 10-10-01...
Page 334 Section 9 Cirrus Design Supplements SR20 Length Conversion Centimetres Into Inches Centimetres En Pouces inch inch inch inch inch inch inch inch inch inch 0.39 0.79 1.18 1.58 1.97 2.36 2.76 3.15 3.54 3.94 4.33 4.72 5.12 5.51 5.91 6.30 6.70...
Page 335 Cirrus Design Section 9 SR20 Supplements Length Conversion Centimetres x 0.394 = Inches Inches x 2.54 = Centimeters INCHES CENTIMETERS Units x 10, 100, etc SR20_FM09_1989 Figure - 2 Sheet 4 of 4 P/N 11934-S17 7 of 14 Original: 10-10-01...
Page 336 Section 9 Cirrus Design Supplements SR20 Distance Conversion Statute Miles x 1.609 = Kilometers Kilometers x 0.622 = Statute Miles Statute Miles x 0.869 = Nautical Miles Nautical Miles x 1.15 = Statute Miles Nautical Miles x 1.852 = Kilometers Kilometers x 0.54 = Nautical Miles...
Page 337 Cirrus Design Section 9 SR20 Supplements Temperature Conversion • Note • • To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns, the number representing the temperature value (°C) to be converted. The equivalent Fahrenheit temperature is read to the right.
Page 338 Section 9 Cirrus Design Supplements SR20 Volume Conversion Litres Into Imperial Gallons Litres En Gallons Impérial Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. Gal. 0.22 0.44 0.66 0.88 1.10 1.32 1.54 1.76 1.98 2.20 2.42 2.64 2.86 3.08 3.30...
Page 339 Cirrus Design Section 9 SR20 Supplements Volume Conversion Imperial Gallons x 4.546 = Litres Litres x 0.22 = Imperial Gallons Imperial Gallons x 1.2 = U.S. Gal. U.S. Gal. x 0.833= Imperial Gallons U.S. Gallons x 3.785 = Litres Litres x 0.264 = U.S. Gallons...
Page 340 Section 9 Cirrus Design Supplements SR20 Volume to Weight Conversion AVGAS (Specific Gravity = 0.72) Litres x 0.72 = Kilograms Kilograms x 1.389 = Litres Litres x 1.58 = Pounds Pounds x 0.633 = Litres LITRES POUNDS LITRES KILOGRAMS Units x 10, 100, etc...
Page 341 Cirrus Design Section 9 SR20 Supplements Quick Conversions In a world of U.S., Imperial, and metric measures, below is a quick way to convert from one system to another. Follow arrow and multiply; backtrack the arrow and divide. Bear in mind that the figures are...
Page 342 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 14 of 14 P/N 11934-S17 Original: 10-10-01...
Page 343 GPSS When the S-Tec System Thirty Autopilot with GPSS is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 344 Section 9 Cirrus Design Supplements SR20 GPSS GPSS SWITCH TRIM ST HD TURN COORDINATOR 2 MIN SR20_FM09_1515 TURN COORDINATOR Figure - 1 System 30 Autopilot 2 of 14 P/N 11934-S19 Revision 1: 12-07-04...
Page 345 Cirrus Design Section 9 SR20 Supplements Section 1 - General This airplane is equipped with an S-TEC System Thirty Autopilot. This two-axis autopilot system receives roll axis control inputs from an integral electric turn coordinator and altitude information from an altitude transducer plumbed into the pitot-static system.
Page 346 Section 9 Cirrus Design Supplements SR20 Section 2 - Limitations 1. Autopilot operation is prohibited above 180 KIAS. 2. The autopilot must not be engaged for takeoff or landing. 3. The autopilot must be disengaged for missed approach, go- around, and balked landing.
Page 347 Cirrus Design Section 9 SR20 Supplements Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the basic Handbook. Do not reengage the autopilot until the malfunction has been identified and corrected. • Note • A GPSS malfunction will most likely affect the autopilot HD (Heading) mode, rendering it unusable.
Page 348 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and its modes. Autopilot Pre-Flight Test 1. Battery Master Switch ............... ON 2. Avionics Power Switch .............. ON Note that all autopilot annunciators illuminate.
Page 349 Cirrus Design Section 9 SR20 Supplements Press and release the GPSS/HDG switch. GPSS will go out and HDG will come on. 5. Altitude Hold ................TEST a. Depress either pilot’s or copilot’s A/P ALT HOLD button (control yoke). Note that ALT (Altitude Hold) light illuminates.
Page 350 Section 9 Cirrus Design Supplements SR20 d. Depress either pilot’s or copilot’s A/P ALT HOLD button (control yoke). Note that ALT (Altitude Hold) light illuminates. e. Press Pilot A/P DISC/Trim Switch (control yoke). Note that the autopilot disengages. Move control yoke to confirm that pitch and roll control is free with no control restriction or binding.
Page 351 Cirrus Design Section 9 SR20 Supplements Manually flying the airplane off the selected altitude will not disengage altitude hold and the autopilot will command a pitch change to recapture the altitude when the control input is released. Illumination of either the TRIM UP or the TRIM DN annunciator indicates the airplane is out of trim and must be manually trimmed in the direction indicated.
Page 352 Section 9 Cirrus Design Supplements SR20 The autopilot will automatically track to the active waypoint anytime GPS 1 has a valid waypoint programmed and the pilot selects GPSS with the autopilot in the HD (Heading) mode. When operating in the GPSS mode, the autopilot does not use inputs from the HSI HDG knob or course control;...
Page 353 Cirrus Design Section 9 SR20 Supplements c. Lead the airplane around the procedure turn or holding pattern using the HSI HDG knob. d. When approaching the desired inbound course, once again select GPSS. e. Conduct remainder of the approach in the GPSS mode.
Page 354 Section 9 Cirrus Design Supplements SR20 Section 7 - Systems Description The airplane is equipped with an S-Tec System Thirty two-axis Automatic Flight Control System (Autopilot). The autopilot roll axis uses an inclined gyro in the turn coordinator case as the primary turn and roll rate sensor.
Page 355 Cirrus Design Section 9 SR20 Supplements RDY (Ready) Light – Illuminates green when autopilot is ready for engagement. When the airplane’s Batt Master switch is turned on and the rate gyro RPM is correct, the green RDY light comes on indicating the autopilot is ready for the functional check and operation.
Page 356 Section 9 Cirrus Design Supplements SR20 and the pilot should manually trim the airplane in the direction indicated. If the pilot fails to trim the airplane, the TRIM UP or TRIM DN light, as applicable, will flash. Both light are out if the airplane is in trim.
Page 357 Selector/Alerter is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 358 The autopilot makes roll changes through the aileron trim motor and spring cartridge and makes pitch changes for altitude hold through the elevator trim motor. The SR20 installation of the S-Tec System 55X Autopilot features: • Heading Hold and Command;...
Page 359 Cirrus Design Section 9 SR20 Supplements this installation does not utilize a CWS (Control Wheel Steering) switch or an AUTOPILOT MASTER switch. • Note • This installation utilizes the airplane’s roll trim actuator to affect steering changes. Therefore, the automatic trim function of the System 55X is not implemented.
Page 360 Section 9 Cirrus Design Supplements SR20 e. The intercept of the localizer shall occur at least 5 miles outside of the outer marker. If the crosswind component is greater than 12 knots and less than 17 knots, the intercept shall occur at least 10 miles outside of the outer marker.
Page 361 Cirrus Design Section 9 SR20 Supplements SR20_FM09_1502A Figure - 1 System 55X Altitude Selector/Alerter & Autopilot Computer P/N 11934-S20 5 of 24 Revision 2: 12-07-04...
Page 362 SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1. Pressing the A/P DISC/Trim switch on the control yoke handle.
Page 363 Cirrus Design Section 9 SR20 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
Page 364 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot and altitude selector and their respective modes. The Autopilot is integrated with the Altitude Selector/Alerter and can be operated with or without data inputs from the Altitude Selector/ Alerter.
Page 365 Cirrus Design Section 9 SR20 Supplements c. Rotate altitude selector input knob to set BARO to the nearest 0.1 inch Hg. d. Push ALT button to display ALT SEL. With a flashing SEL annunciator, rotate the selector knob to input an altitude 300 to 400 feet lower or higher than the indicated altitude.
Page 366 Section 9 Cirrus Design Supplements SR20 c. Altitude Hold ..............TEST 1.) Depress ALT button on autopilot programmer/computer. Note that ALT annunciator comes on, VS annunciator goes out, and yoke does not move. d. Overpower Test: 1.) Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot.
Page 367 Cirrus Design Section 9 SR20 Supplements 3. Use HSI HDG bug to make heading changes as desired. Autopilot Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected.
Page 368 Section 9 Cirrus Design Supplements SR20 3. Press the VS button on the autopilot programmer/computer to engage the vertical speed mode. When the mode is engaged, the autopilot will synchronize to and hold the vertical speed at the time the mode was engaged.
Page 369 Cirrus Design Section 9 SR20 Supplements 4. Press DTA again to accept altitude entry, the ENT annunciator will go out and the SEL annunciator will stop flashing and illuminate steady indicating that the system is in the ‘operate’ mode. • Note •...
Page 370 Section 9 Cirrus Design Supplements SR20 BARO Selection Upon initial start-up, the altitude selector enters BARO select immediately after the self-test if it is receiving a valid altitude signal. The setting can easily be entered at this time. At other times, it is necessary to select the DTA entry and BARO modes in order to adjust the BARO setting.
Page 371 Cirrus Design Section 9 SR20 Supplements is set. As the airplane approaches within approximately 50 feet of the decision height, the alert will sound and the DH light will flash. As the airplane passes through approximately 50 feet beyond the decision height, the alert will sound and the light will flash again.
Page 372 Section 9 Cirrus Design Supplements SR20 the autopilot programmer/computer (NAV, HDG, and GPSS will be displayed). When the on-course intercept turn begins the HDG mode will disengage and the annunciator will go out. During the intercept sequence, the autopilot operates at maximum gain and sensitivity (90% of standard rate turn).
Page 373 Cirrus Design Section 9 SR20 Supplements Glideslope Intercept and Tracking 1. Begin with a reliable ILS signal selected on the NAV receiver. 2. Select autopilot NAV and APR. Airplane must be within 50% needle deviation of localizer centerline. 3. Select ALT mode. Airplane must be 60% or more below the glideslope centerline during the approach to the intercept point.
Page 374 Section 9 Cirrus Design Supplements SR20 steering is accomplished by autopilot steering commands to the aileron trim motor and spring cartridge. The pitch computer receives altitude data from the altitude encoder pressure transducer plumbed into the static system, an accelerometer, and glideslope information from the HSI and #1 NAV radio.
Page 375 Cirrus Design Section 9 SR20 Supplements HDG (Heading) Mode – When HDG is selected, the autopilot will engage the HDG mode, fly the airplane to, and hold the heading set on the HSI. Subsequent heading changes are made using the HDG knob on the HSI.
Page 376 Section 9 Cirrus Design Supplements SR20 GS (Glideslope) – The autopilot GS function will capture and track an ILS glideslope. To arm the GS function, the following conditions must be met: (1) the NAV receiver must be tuned to the appropriate ILS frequency;...
Page 377 Cirrus Design Section 9 SR20 Supplements Altitude Selector / Alerter The altitude selector / alerter provides the autopilot with an altitude preselect function, a programmable vertical speed function, as well as provides altitude alert, decision height alert, and baro corrected altitude display.
Page 378 Section 9 Cirrus Design Supplements SR20 DTA (Data) – The data entry button is used to select data entry mode. The first time the DTA button is pressed the selector will enter the data entry mode, the ENT annunciator will come on, and the SEL annunciator will flash to indicate the system is ready to accept an altitude entry.
Page 379 Cirrus Design Section 9 SR20 Supplements ALT (Altitude) – The ALT button has two functions: Altitude Pre-select and Altitude readout. Pre-select - When the ALT button is pressed while the system is in the Data Entry (DTA) mode the SEL annunciator will flash and a new altitude can be selected by rotating the input knob CW to increase altitude and CCW to decrease altitude in thousands of feet.
Page 380 Section 9 Cirrus Design Supplements SR20 DH (Decision Height) – The DH button allows entry and arming of altitude alerting at a set decision height. To set a DH, first enter the data (DTA) entry (ENT) mode, press the DH button, and rotate the selector knob to input the desired decision height to the nearest 100 feet above the specified decision height.
Page 381 When the Avidyne FlightMax EX-Series 700-00004-XXX-() Multi- Function Flight Display (MFD) with software partnumber 530-00112- 000 or later is installed in the Cirrus Design SR20, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 382 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with an Avidyne FlightMax EX-Series 700- 00004-XXX-() Multi-Function Flight Display (MFD). The MFD is a 10.4- inch landscape-oriented display mounted in the instrument panel. The MFD provides supplemental display of situational and navigation information to the pilot.
Page 383 Cirrus Design Section 9 SR20 Supplements Figure - 1 Avidyne FlightMax Multifunction Display P/N 11934-S21 3 of 12 Revised: 09-27-04...
Page 384 Section 9 Cirrus Design Supplements SR20 Section 2 - Limitations 1. The moving map display must not be used as the primary navigation instrument. The moving map display provides visual advisory of the airplane’s GPS position against a moving map.
Page 385 Cirrus Design Section 9 SR20 Supplements Serials with EX5000C MFD installed: The Avidyne FlightMax EX5000C Pilot’s Guide, P/N 600-00108-000, Revision 03 or later, must be available to the pilot during all flight operations. Section 3 - Emergency Procedures No Change...
Page 386 Section 9 Cirrus Design Supplements SR20 Section 6 - Weight & Balance Installation of the Avidyne FlightMax MFD adds the following optional (Sym = O) equipment at the weight and arm shown in the following table. The adapter plate is used only on most installations where the MFD was installed by Service Bulletin.
Page 387 Cirrus Design Section 9 SR20 Supplements The Jeppesen NavData database provides data on airports, approaches, VORs, NDB, intersections, airspace definitions, and frequencies. North American and international databases are available. Database information can be updated through the USB port on the front bezel.
Page 388 Section 9 Cirrus Design Supplements SR20 Checklist The Normal and Emergency Procedures Checklists in the MFD are interactive. The pilot is able to check off each step as it is accomplished. Once a step is checked off, it changes color so that a record of completed steps is visually recorded.
Page 389 Cirrus Design Section 9 SR20 Supplements Setup Various System Setup pages allow the pilot to set user preferences for system operation. In addition to listing the software version identification information and database validity dates, the System Setup pages allow access to several pages for preference selection.
Page 390 Section 9 Cirrus Design Supplements SR20 XM Satellite Weather System (Optional Installation) • WARNING • Do not use the XM Satellite Weather System for navigation of the aircraft. The XM Satellite Weather System is intended to serve as a situational awareness tool only.
Page 391 Cirrus Design Section 9 SR20 Supplements CMax Approach Charts (Optional Installation) • WARNING • Do not use the CMax Approach Charts function for navigation of the aircraft. The CMax Approach Charts function is intended to serve as a situational awareness tool only. The electronic approach charts must not be used as the primary set of on-board approach charts.
Page 392 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 12 of 12 P/N 11934-S21 Revised: 09-27-04...
Page 393 Garmin GNS 430 GPS Navigator When a Garmin GNS 430 GPS Navigator with NAV, ILS, and COM is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 394 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a Garmin GNS 430 GPS Navigator with VHF Nav, ILS, and VHF Com herein referred to as the “Navigator.” The GNS 430 is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
Page 395 Cirrus Design Section 9 SR20 Supplements Section 2 – Limitations Provided the GPS Navigator is receiving adequate usable signals, it has been demonstrated capable of and has been shown to meet the accuracy specifications of: 1. VFR/IFR, enroute, terminal, and instrument approach (GPS, VOR) operations, that is, enroute, terminal, and instrument approach within the U.S.
Page 396 Section 9 Cirrus Design Supplements SR20 6. The aircraft must have other approved navigation equipment installed and operating appropriate to the route of flight. Section 3 - Emergency Procedures 1. If GPS Navigator information is not available or is invalid, utilize remaining operational navigation equipment as required.
Page 397 GNS 430 Integration The GNS 430 Navigator is integrated into the SR20 Avionics installation in three configurations: 1. Single GARMIN GNS 430 (GPS 1) interfaced with the CDI and MFD and a single GARMIN GNC 250XL (GPS 2) not integrated with a remote indicator.
Page 398 GPS 2 in this configuration is a GARMIN GNC 420 GPS Navigator interfaced with the CDI (VOR/LOC Indicator). This unit displays GPS data on the unit’s display panel and on the remote CDI (VOR/LOC Indicator). Refer to the SR20 POH Supplement for GARMIN GNC 420 GPS Navigator, P/N 11934-S23.
Page 399 • Note • This supplement provides a general description of the Garmin GNS 430, its operation, and SR20 interface. For a detailed description of the GNS 430 and full operation instructions refer to the Garmin GNS 430 Pilot's Guide and Reference, P/N 190- 00140-00, Revision F dated July 2000 (or later appropriate revision).
Page 400 Section 9 Cirrus Design Supplements SR20 center console. The GPS is designated ‘GPS 1.’ A VHF NAV receiver and tuner for receiving VHF Omnirange (VOR), Localizer (LOC), and Glideslope (G/S) is also integrated into the control unit. The NAV receiver is designated ‘NAV 1.’ Additionally, a VHF communications receiver, designated ‘COM 1,’...
Page 401 Cirrus Design Section 9 SR20 Supplements Navigation (Nav) Receiver The Garmin GNS 430 provides an integrated Navigation (NAV) receiver with VHF Omnirange/Localizer (VOR/LOC) and Glideslope (G/S) capability. The VOR/LOC receiver receives on a frequency range from 108.000 Mhz to 117.950 Mhz with 50 kHz spacing.
Page 402 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 10 of 10 P/N 11934-S22 Original: 01-07-03...
Page 403 Garmin GNC 420 GPS Navigator When a GARMIN GNC 420 GPS Navigator with VHF COM is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 404 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a GARMIN GNC 420 GPS Navigator with VHF Com herein referred to as the “Navigator.” The GNC 420 is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
Page 405 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. The GARMIN GNC 420 Pilot's Guide and Reference, P/N 190- 00140-20, Revision B dated August 2002 (or later appropriate revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the GPS Navigator.
Page 406 Section 9 Cirrus Design Supplements SR20 Section 3 - Emergency Procedures 1. If GPS Navigator information is not available or is invalid, utilize remaining operational navigation equipment as required. 2. If "RAIM NOT AVAILABLE…" or “RAIM POSITION WARNING” message is displayed, continue to navigate using the GPS equipment or revert to an alternate means of navigation appropriate to the route and phase of flight.
Page 407 • Note • This supplement provides a general description of the GARMIN GNC 420, its operation, and SR20 interface. For a detailed description of the GNC 420 and full operation instructions refer to the GARMIN GNC 420 Pilot's Guide and Reference, P/N 190-00140-20, Revision B dated August 2002 (or later appropriate revision).
Page 408 Section 9 Cirrus Design Supplements SR20 GPS Navigator The GARMIN GNC 420 GPS navigator is the secondary system (GPS 2), is IFR certified, and is coupled to the airplane’s CDI. The GARMIN GNC 420 GPS navigator is capable of providing IFR enroute, terminal, and approach navigation with position accuracies better than 15 meters.
Page 409 Cirrus Design Section 9 SR20 Supplements frequency display window is at the upper left corner of the GNC 420 display. Auto-tuning can be accomplished by entering a frequency from a menu. The COM 2 antenna is located below the cabin on the airplane centerline.
Page 410 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 8 of 8 P/N 11934-S23 Original: 01-07-03...
Page 411 Display When a Sandel Avionics SN3308 Navigation Display is installed in the Cirrus Design SR20, serials 1268 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 412 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with a Sandel SN3308 navigation display. This SN3308 is a three-inch instrument installed in the pilot’s instrument panel, which performs the functions of a standard HSI combined with a two-pointer RMI.
Page 413 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. The Sandel Avionics SN3308 Navigation Display Pilot's Guide, SPN 90106-PG-C or later revision, must be immediately available to the flight crew when navigation is predicated on use of the Sandel SN3308 Navigation Display.
Page 414 Section 9 Cirrus Design Supplements SR20 3. The Navigation display will be active and capable of displaying data from either VOR-ILS or GPS. a. Selection of the primary navigation source between VOR-ILS 1 and GPS 1 is accomplished by pressing the NAV switch on the left side of the SN3308 Navigation Display to connect the navigation source to the HSI course pointer and the autopilot.
Page 415 Cirrus Design Section 9 SR20 Supplements the display. Redundant power sources provide 28 VDC for system operation. Power is supplied through the 5-amp HSI/PFD #1 circuit breaker on the Essential Bus and the 5-amp HSI/PFD #2 circuit breaker on Main Bus 2. Either circuit is capable of powering the Navigation Display.
Page 416 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 6 of 6 P/N 11934-S24 Original: 01-07-03...
Page 417 Winterization Kit When the Winterization Kit Inlet covers are installed in accordance with SB 2X-71-04 R3, Cirrus Design drawing 70027, or Cirrus Design drawing 70102, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot's Operating Handbook.
Page 418 Section 9 Cirrus Design Supplements SR20 Section 1 - General This airplane is equipped with removable cowl inlet airflow restrictors. Figure 1 shows installation instructions. Section 2 - Limitations Winterization Kit 1. The airplane must not be operated above 32°F when the Winterization Kit cowl inlet covers (airflow restrictors) are installed.
Page 419 Cirrus Design Section 9 SR20 Supplements Section 4 - Normal Procedures Install Cowl Inlet Airflow Restrictor (See Figure 1) 1. Loosen screw securing latch plate to inlet cover and slide latch plate inboard. 2. Position inlet cover in inlet. 3. Slide latch plate outward (behind edge of cowl) and tighten screw.
Page 420 Section 9 Cirrus Design Supplements SR20 Serials 1005 through 1422. LEGEND Serials 1423 and subsequent. 1. Cowl Inlet Cover 2. Latch Plate 3. Screw SR20_FM09_1516A Figure - 1 Cowl Inlet Installation 4 of 6 P/N 11934-S25 Revision 1: 12-07-04...
Page 421 Cirrus Design Section 9 SR20 Supplements Section 5 - Performance No Change. Section 6 - Weight & Balance Change is Negligible. Section 7 - Systems Description • Caution • Use of the inlet cover airflow restrictors above 32° F (0° C) ambient temperature may result in CHT and Oil Temperatures above the red line.
Page 422 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 6 of 6 P/N 11934-S25 Revision 1: 12-07-04...
Page 423 When the Avidyne FlightMax Entegra Primary Flight Display (PFD) with Software Version 530-00123-XXX or 530-00159-XXX (where X can be any digit from 0 to 9) is installed in the Cirrus Design SR20 serials 1337 and subsequent, this POH Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 424 Section 9 Cirrus Design Supplements SR20 Section 1 - General The airplane is equipped with an Avidyne FlightMax Entegra-Series Primary Flight Display (PFD). The PFD is a 10.4” landscape-oriented display intended to be the primary display of primary flight parameter information (attitude, airspeed, heading, and altitude) to the pilot.
Page 425 Cirrus Design Section 9 SR20 Supplements Figure - 1 Primary Flight Display P/N 11934-S26 3 of 16 Revision 2: 12-07-04...
Page 426 Section 9 Cirrus Design Supplements SR20 Section 2 - Limitations 1. The PFD integrates with separately approved sensor installations. Adherence limitations appropriate installation supplements is mandatory. 2. The Avidyne FlightMax Entegra-Series PFD Pilot’s Guide, P/N 600-00081-000, Revision 03, or latest revision, must be available to the pilot during all flight operations.
Page 427 Cirrus Design Section 9 SR20 Supplements • WARNING • Autopilot may not be able to maintain all selectable vertical speeds. Selecting a vertical speed that exceeds the aircraft’s available performance may cause the aircraft to stall. 12. Minimum speed with the autopilot engaged is 1.2V for the given configuration.
Page 428 Section 9 Cirrus Design Supplements SR20 Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation. Those minimum items of equipment necessary under the operating rules are defined in 14 CFR Part 91 and 14 CFR Part 135 as applicable.
Page 429 Cirrus Design Section 9 SR20 Supplements Section 3 - Emergency Procedures • Note • Dim brightness level to black if PFD is found distracting. In the unlikely event of a PFD failure, the pilot may lose the ability to control the autopilot through the PFD controls. If this...
Page 430 Section 9 Cirrus Design Supplements SR20 Loss of Attitude Data • WARNING • Aircraft equipped with Software Version 530-00123-000 Rev 00 or higher; Any power interruption to the PFD will result in loss of attitude information until the PFD can be restarted on the ground.
Page 431 Cirrus Design Section 9 SR20 Supplements Section 4 - Normal Procedures Activate PFD 1. PFD Circuit Breakers ..............IN 2. Bat/Alt Master Switches .............ON De-Activate PFD 1. Bat/Alt Master Switches ............OFF 2. PFD Circuit Breakers ............. PULL Section 5 - Performance No Change.
Page 432 Section 9 Cirrus Design Supplements SR20 Section 7 - System Description • Note • This supplement provides a general description of the Avidyne FlightMax Entegra-Series Primary Flight Display, its operation, and airplane interface. For a detailed description of the PFD, refer to the Avidyne FlightMax Entegra-Series PFD Pilot’s...
Page 433 Cirrus Design Section 9 SR20 Supplements PFD 2 MAIN BUS 2 PFD 1 ESSENTIAL BUS #1 GNS-430 PITOT STATIC Avidyne PFD #2 GNS-430 OAT Sensor / Magnetometer Flight Director System (Optional) STEC System 55x Autopilot Avidyne MFD SR20_FM09_1607A Figure - 2...
Page 434 Section 9 Cirrus Design Supplements SR20 Attitude Direction Indicator (ADI) Air Data The airspeed tape to the left of the main ADI begins indicating at 20 Knots Indicated Airspeed (KIAS) and is color-coded to correspond with airspeeds for V , and V .
Page 435 Cirrus Design Section 9 SR20 Supplements Navigation Data Navigation data on the PFD takes several forms. A course deviation indicator (CDI) is always provided on the HSI and a bearing pointer can be optionally selected for display on the HSI by the pilot. Controls...
Page 436 Section 9 Cirrus Design Supplements SR20 In flight director equipped aircraft, when a vertical mode of the autopilot is being used, a set of flight director command bars will indicate the required steering of the aircraft to achieve the commanded tracking from the autopilot.
Page 437 Cirrus Design Section 9 SR20 Supplements Flight Director System (Optional Installation) • Note • For a detailed description of the Flight Director system, refer to Avidyne FlightMax Entegra-Series PFD Pilot’s Guide, P/N 600-00081-000, Revision 08, or later revision. The Flight Director system enhances situational awareness by reducing cockpit workload through providing a visual cue for the pilot to follow as indicated by the PFD’s Flight Director Steering Command...
Page 438 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 16 of 16 P/N 11934-S26 Revision 2: 12-07-04...
Page 439 Cirrus Design SR20, serials 1337 and subsequent, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 440 • Note • The SR20 implementation of the System 55SR Autopilot does not utilize the optional remote annunciator, roll servo, yaw servo. Therefore, all references to these items in the S-Tec System 55SR POH shall be disregarded.
Page 441 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Autopilot operation is prohibited above 180 KIAS. 2. The autopilot must not be engaged for takeoff or landing. 3. The autopilot must be disengaged for missed approach, go- around, and balked landing.
Page 442 Section 9 Cirrus Design Supplements SR20 The flaps should be extended in the approach configuration prior to the Outer Marker. No further changes in the flap configuration should be made throughout the autopilot- coupled approach. 10. The S-Tec System 55SR Autopilot Pilot’s Operating Handbook (POH), P/N 87127 dated 01 September 2003 or later, must be carried in the airplane and available to the pilot while in flight.
Page 443 Cirrus Design Section 9 SR20 Supplements S-TEC FIFTY FIVE SR REV TRIM VS + VS x 100 SR20_FM09_1996 Figure - 1 System Fifty-Five SR Autopilot P/N 11934-S27 5 of 16 Revision 1: 12-07-04...
Page 444 SR20 Section 3 - Emergency Procedures Autopilot Malfunction Refer to Electric Trim/Autopilot Failure procedure in the SR20 POH. Do not reengage the autopilot until the malfunction has been identified and corrected. The autopilot may be disconnected by: 1. Pressing the A/P DISC/Trim switch on the control yoke handle.
Page 445 Cirrus Design Section 9 SR20 Supplements System Failure and Caution Annunciations If any of the following failure annunciations occur at low altitude or during an actual instrument approach, disengage the autopilot, execute a go-around or missed approach as appropriate. Inform ATC of problem.
Page 446 Section 9 Cirrus Design Supplements SR20 Section 4 - Normal Procedures Refer to Section 7 – Systems Description for a description of the autopilot modes. • WARNING • The pilot must properly monitor and control the engine power to avoid stalling the airplane in autopilot altitude hold or vertical speed modes.
Page 447 Cirrus Design Section 9 SR20 Supplements e. Altitude Hold ..............TEST 1.) Depress ALT button on autopilot programmer/computer. Note that ALT annunciator comes on, VS annunciator goes out, and yoke does not move. Overpower Test: 1.) Grasp control yoke and input left aileron, right aileron, nose up, and nose down to overpower autopilot.
Page 448 Section 9 Cirrus Design Supplements SR20 3. Use the HDG bug to make heading changes as desired. Autopilot Altitude Hold Mode 1. Manually fly the airplane to the desired altitude and level off. • Note • For smoothest transition to altitude hold, the airplane rate of climb or descent should be less than 100 FPM when Altitude Hold is selected.
Page 449 Cirrus Design Section 9 SR20 Supplements Autopilot Vertical Speed Mode 1. Begin by manually establishing the desired vertical speed. 2. Press HDG or NAV to engage a roll mode. The associated annunciator will illuminate. • Note • A roll mode must be engaged prior to engaging a pitch mode.
Page 450 Section 9 Cirrus Design Supplements SR20 • Note • If the course needle is at full-scale deviation, the autopilot will establish the airplane on a heading for a 45° intercept with the selected course. As the airplane approaches the course, the autopilot will smoothly shallow the intercept angle.
Page 451 Cirrus Design Section 9 SR20 Supplements • Note • If the HDG bug is within 5° of center and the course deviation is less than 10%, the autopilot will immediately establish the lowest level of sensitivity and limit the turn rate to a maximum of 25% of a standard rate turn.
Page 452 Section 9 Cirrus Design Supplements SR20 All Autopilot mode selection is performed by using the mode select buttons and VS knob on the autopilot programmer/computer in the center console. Annunciators in the programmer/computer display window annunciate modes. Refer to Figure 1 for an illustration of the programmer/computer.
Page 453 Cirrus Design Section 9 SR20 Supplements APR (Approach) – When APR is selected, the autopilot provides increased sensitivity for VOR or GPS approaches. APR may also be used to provide increased sensitivity for enroute course tracking. ALT (Altitude Hold), Mode – When ALT is selected, the autopilot will hold the altitude at the time the mode was selected.
Page 454 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 16 of 16 P/N 11934-S27 Revision 1: 12-07-04...
Page 455 Supplement Garmin GTX 330 Mode S Transponder When a Garmin GTX 330 Transponder is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook.
Page 456 Section 9 Cirrus Design Supplements SR20 GARMIN GTX 330 IDENT FLIGHT TIME CRSR FUNC 1200 01:23:20 START STOP 1. Identification Key 5. CRSR (Cursor) 2. Mode Selector Keys 6. CLR (Clear) Key a. OFF 7. START/STOP Key b. STBY (Standby) 8.
Page 457 Cirrus Design Section 9 SR20 Supplements Section 1 - General The airplane is equipped with a single Garmin GTX 330 ATC Mode S transponder with IDENT capability. This supplement provides complete operating instructions for the GTX 330 and does not require any additional data be carried in the airplane.
Page 458 • Note • This supplement provides specific procedures for use of the GTX 330 Transponder in the SR20 and a general description of the unit. For a detailed description of the GTX 330, refer to GARMIN GTX 330 Mode S Transponder Pilots Guide, p/n 190-00207-00 Revision A (Sept 2002) or later revision.
Page 459 Cirrus Design Section 9 SR20 Supplements While providing the usual identification code and pressure altitude information as Mode A and C transponders, the Mode S transponder also uses a unique aircraft address to enhance the tracking capabilities of ATC and other Mode S transponder-equipped aircraft.
Page 460 Section 9 Cirrus Design Supplements SR20 reply to any interrogations from an ATC secondary ground surveillance radar system. This is the normal position for ground operations in the SR20. • Note • Depend on the ATC environment, STBY or GND mode is automatically entered from ALT or ON mode during landing ground roll as the groundspeed decreases through 35 knots.
Page 461 Cirrus Design Section 9 SR20 Supplements CRSR key during code entry will remove the cursor and cancel the entry. • Note • When making routine code changes, avoid inadvertent selection of code 7500 and all codes within the 7600 series (7600 –...
Page 462 Section 9 Cirrus Design Supplements SR20 Flight Time, Count Up Timer, Count Down Timer, Contrast, and Display Brightness. START/STOP Key - Starts and stops the Altitude Monitor, Count Up, Count Down, and Flight timers. In Configuration Mode, steps through functions in reverse.
Page 463 Supplement SR20 Airplanes Registered in the European Union 1. This supplement is required for operation of Cirrus Design SR20 airplane serial numbers 1005 and subsequent when registered in the European Union. This supplement must be attached to the applicable SR20 EASA/FAA-approved Airplane Flight Manual.
Page 464 Section 9 Cirrus Design Supplements SR20 Section 1 - General No Change. Section 2 - Limitations Two-blade propellers are not EASA approved for use on this airplane. Ignore all references to the two-blade propeller in this Pilot’s Operating Handbook. Amend “Propeller” limitation to read as follows: Hartzell Propeller Type..............
Page 465 Cirrus Design Section 9 SR20 Supplements Section 8 - Handling, Servicing & Maintenance No Change. Section 9 - Supplements No Change. Section 10 - Safety Information No Change. P/N 11934-S29 3 of 4 Original: 05-27-04...
Page 466 Section 9 Cirrus Design Supplements SR20 Intentionally Left Blank 4 of 4 P/N 11934-S29 Original: 05-27-04...
Page 467 Awareness Warning System When the Honeywell KGP 560 Terrain Awareness and Warning System is installed in the Cirrus Design SR20, this Supplement is applicable and must be inserted in the Supplements Section (Section 9) of the Cirrus Design SR20 Pilot’s Operating Handbook. This document must be carried in the airplane at all times.
Page 468 MFD. For specific MFD operational details, refer to the Cirrus Design Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual Supplement For Avidyne EX-Series Multifunction Flight Display, P/N 11934-S18 or 11934-S21, Original Release or later.
Page 469 Cirrus Design Section 9 SR20 Supplements Section 2 - Limitations 1. Do not use the Terrain Awareness Display for navigation of the aircraft. The KGP 560 Terrain Awareness and Warning System is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
Page 470 Section 9 Cirrus Design Supplements SR20 Activate TAWS • Note • If the aircraft horizontal position derived from the Garmin Navigator (GPS 1) is invalid, TAWS will be inoperative and the TERR INOP annunciator will illuminate. 1. SKYWATCH/TAWS Circuit Breaker..........IN 2.
Page 471 Cirrus Design Section 9 SR20 Supplements Response To Awareness Alerts Aural “TERRAIN AHEAD” Alert Aural “OBSTACLE AHEAD” Alert Amber TERR CAUT Annunciation 1. Take positive corrective action until the alert ceases. Stop descending, or initiate a climb turn as necessary, based on analysis of all available instruments and information.
Page 472 Section 9 Cirrus Design Supplements SR20 Section 7 - Systems Description The Honeywell KGP 560 Terrain Awareness and Warning System compares GPS information from the Garmin Navigator (GPS 1) to the integrated Terrain/Obstacle Database to produce a real-time model of the surrounding terrain.
Page 473 Cirrus Design Section 9 SR20 Supplements GNS-430 TAWS Annunciator Panel GMA 340 Audio Panel Avidyne PFD KGP 560 Processor Transponder Avidyne MFD TAWS AVIONICS NON-ESSENTIAL Configuration Module SR20_FM09_2031 Figure - 1 Honeywell KGP 560 TAWS Simplified Schematic P/N 11934-S30 7 of 12...
Page 474 Section 9 Cirrus Design Supplements SR20 TAWS Annunciator Panel TAWS terrain annunciations and control functions are incorporated into the Annunciator Panel. The panel consists of a momentary pushbutton switch (SELF TEST), an illuminated pushbutton switch (TERR INHIBIT), and three LEDS for Terrain Warning (TERR WARN), Terrain Caution (TERR CAUT), Terrain Inoperative (TERR INOP).
Page 475 Cirrus Design Section 9 SR20 Supplements TAWS SELF TERR TERR TERR TERR TEST INHIBIT INOP CAUT WARN SR20_FM09_2033 Annunciator Color Function SELF TEST Provides test function for TAWS TERR INHIBIT AMBER All TAWS alerting functions inhibited TERR INOP AMBER Indicates TAWS inoperative...
Page 476 Section 9 Cirrus Design Supplements SR20 MFD Terrain Awareness Display • WARNING • Do not use the Terrain Awareness Display for navigation of the aircraft. The TAWS is intended to serve as a situational awareness tool only and may not provide the accuracy fidelity on which to solely base terrain or obstacle avoidance maneuvering decisions.
Page 477 Cirrus Design Section 9 SR20 Supplements Geometric Altitude versus Measured Sea Level An indication of MSL-G or Geometric Altitude may appear on the left side of the MFD indicating the height above Measured Sea Level (MSL) calculated from the GPS.
Page 478 Section 9 Cirrus Design Supplements SR20 Self Test Proper operation of the TAWS can be verified when the aircraft is on the ground as follows: 1. Select the TAWS page on the MFD 2. Clear all caution messages in the lower right corner 3.
Page 479 Cirrus Design Section 10 SR20 Safety Information Section 10 Safety Information Table of Contents Introduction ................... 10-3 Cirrus Airframe Parachute System (CAPS) Deployment ....10-4 Deployment Scenarios............... 10-4 Mid-air Collision ..............10-4 Structural Failure ..............10-4 Loss of Control ............... 10-5 Landing Required in Terrain not Permitting a Safe Landing...
Page 480 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-2 P/N 11934-003 Reissue A...
Page 481: Introduction
SR20 Safety Information Introduction The Cirrus Design SR20 is a modern, advanced technology airplane designed to operate safely and efficiently in a flight environment. However, like any other aircraft, pilots must maintain proficiency to achieve maximum safety, utility, and economy.
Page 482: Cirrus Airframe Parachute System (Caps) Deployment
Instead, possible CAPS activation scenarios should be well thought out and mentally practiced by every SR20 pilot. The following discussion is meant to guide your thinking about CAPS activation.
Page 483: Loss Of Control
Cirrus Design Section 10 SR20 Safety Information continued safe flight and landing. If it is not, CAPS activation should be considered. Loss of Control Loss of control may result from many situations, such as: a control system failure (disconnected or jammed controls); severe wake turbulence, severe turbulence causing upset, severe airframe icing, or sustained pilot disorientation caused by vertigo or panic;...
Page 484: Deployment Altitude
Section 10 Cirrus Design Safety Information SR20 if time and altitude are critical, and/or ground impact is imminent, the CAPS should be activated regardless of airspeed. Deployment Altitude No minimum altitude for deployment has been set. This is because the actual altitude loss during a particular deployment depends upon the airplane’s airspeed, altitude and attitude at deployment as well as...
Page 485: Landing Considerations
Cirrus Design Section 10 SR20 Safety Information Landing Considerations After a CAPS deployment, the airplane will descend at less than 1500 feet per minute with a lateral speed equal to the velocity of the surface wind. The CAPS landing touchdown is equivalent to ground impact from a height of approximately 10 feet.
Page 486: Water Landings
Section 10 Cirrus Design Safety Information SR20 If the pilot elects to touchdown with a door opened, there are several additional factors the pilot must consider: loss of door, possibility of head injury, or injury from an object coming through the open door.
Page 487: Post Impact Fire
Cirrus Design Section 10 SR20 Safety Information consider unlatching a door prior to assuming the emergency landing body position in order to provide a ready escape path should the airplane begin to sink. Post Impact Fire If there is no fire prior to touchdown and the pilot is able to shut down the engine, fuel, and electrical systems, there is less chance of a post impact fire.
Page 488 Section 10 Cirrus Design Safety Information SR20 Intentionally Left Blank 10-10 P/N 11934-003 Revision A1...

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